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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 5590. Отображено 100.
09-02-2012 дата публикации

Reinforcing Element for Use with a Ventilator Hub

Номер: US20120034099A1
Автор: Henrik Witt
Принадлежит: Henrik Witt

In order to provide a ventilator hub ( 1 ) having means ( 2, 3 ) for connecting to a ventilator spindle and an essentially cylindrical fastening section ( 4 ) having radial adapters ( 6 ) for a number of ventilator blades, whereby the fastening section ( 4 ) has an inner casing surface ( 5 ) that ensures fastening of the ventilator blades with sufficient tensile strength, even at high temperatures, such as they can occur in tunnel fires, without thereby having an undesirably high mass, it is proposed to provide the ventilator hub with an essentially annular, closed reinforcement element ( 7 ) having means ( 10 ) for fastening the ventilator blades with high tensile strength, that is designed essentially separate from the fastening section ( 4 ).

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Номер записи: 1
24-05-2012 дата публикации

Turbine engine compressor stator

Номер: US20120128497A1
Автор: Carl S. Richardson, Edwin M. Worth, Hope C. Rowley, Paul W. Baumann
Принадлежит: Individual

A gas turbine engine stator segment has a shroud band and a plurality of blade sections. Each of the blade sections has a first section with a first thickness, second section with a second thickness and a fairing section transitioning between the first and second section. The second section thickness is less than the first section thickness.

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Номер записи: 2
12-07-2012 дата публикации

FIBER-REINFORCED Al-Li COMPRESSOR AIRFOIL AND METHOD OF FABRICATING

Номер: US20120177501A1
Автор: Jianqiang Chen, Ronald Ralph Cairo
Принадлежит: General Electric Co

A metal matrix composite lightweight compressor airfoil. The airfoil comprises a braided fabric embedded in a lightweight aluminum-lithium alloy. The airfoils are fabricated by forming a plurality of fiber tows by twisting filaments or fibers. The tows are then braided into a fabric. The fabric may be impregnated with an optional fugitive polymer that temporarily occupies interstices of the fabric to facilitate handling of the pre-formed braided fabric, but which is subsequently removed. The airfoil may then be formed as a MMC by one of two separate methods. In the first method, aluminum-lithium alloy is pressure augmented casting into a die that includes a preform of fabric impregnated with fugitive polymer. In a second method, a preform is formed using a tool and mandrel by impregnating fabric with aluminum-lithium alloy. Then aluminum-lithium alloy is pressure augmented cast into a die that includes the alloy-impregnated preform.

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Номер записи: 3
20-09-2012 дата публикации

Method for producing a metal reinforcement for a turbine engine blade

Номер: US20120233859A1
Автор: Bernard Jose Michel Cattiez, Jerome Guinois, Philippe Marolle, Stephane Andre Leveque, Thierry Jean Emile Flesch
Принадлежит: SNECMA SAS

A method for making a metal reinforcement for the leading edge or trailing edge of a turbine engine blade, including: positioning a preform using an equipment positioning the preform in a position such that the preform, at one end thereof, has an area which is capable of receiving a filler metal; and, after the positioning, constructing a base for the metal reinforcement by hard-surfacing with filler metal in the area, in the form of metal beads.

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Номер записи: 4
20-12-2012 дата публикации

Method for making a metal reinforcement for the blade of a turbine engine

Номер: US20120317810A1
Автор: Dominique Magnaudeix, Gilles Charles Casimir Klein, Philippe Marolle, Stephane Andre Leveque
Принадлежит: SNECMA SAS

A method for making a metal reinforcement for the leading edge or trailing edge of the blade of a turbine engine that includes making a metal insert defining the base of the metal reinforcement; positioning the metal insert at the end of a blank of a shaping tool, the blank repeating the shape of the turbine-engine blade; shaping a planar metal sheet on the metal insert and the blank of the shaping tool using a superplastic hot-shaping method.

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Номер записи: 5
27-12-2012 дата публикации

Observing apparatus and observation method

Номер: US20120327210A1
Автор: Hiroaki Kii
Принадлежит: Nikon Corp

A certain material irregularly expressed in an observation area is effectively observed. An observing apparatus includes a first observing unit performing a time lapse shooting of a predetermined observation area, a first discriminating unit discriminating whether or not a first material is expressed in the observation area based on an image obtained by the first observing unit, and a second observing unit starting a time lapse shooting relating to a part where the first material is expressed at a timing when the first material is expressed in the observation area, in which a shooting frequency of the time lapse shooting by the second observing unit is higher than a shooting frequency of the time lapse shooting by the first observing unit.

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Номер записи: 6
31-01-2013 дата публикации

Acoustic Array of Polymer Material

Номер: US20130025967A1
Автор: David C. Seib
Принадлежит: Dresser Rand Co

The invention is an acoustic liner for attenuating noise in rotating machinery. The acoustic liner may include a plurality of cells coupled together to form an annular cell matrix, the plurality of cells being made of a non-metallic material, for example, plastics, polymers, thermoplastics, or thermosets. Each cell of the acoustic liner may be hexagonally-shaped such that the annular cell matrix forms a honeycomb structure.

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Номер записи: 7
21-03-2013 дата публикации

Wall structure with noise damping insulation properties and gas turbine with such a wall structure

Номер: US20130071231A1
Автор: Antun Svilicic, Eduard Bruhwiler, Marc Rauch, Mladen Matan
Принадлежит: Alstom Technology AG

A wall structure is provided with noise damping insulation properties, for an air intake manifold of a gas turbine. The wall structure includes a first structure for mechanically supporting an outer sheet, which separates the spaces on both sides of the wall in an airtight manner, and further includes a second structure for establishing noise damping insulation between the spaces on both sides of the wall. The second structure is secured to the first structure. A gas turbine including the wall structure is also provided.

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Номер записи: 8
01-08-2013 дата публикации

Aluminum airfoil

Номер: US20130195674A1
Автор: Daniel A. Bales, Thomas J. Watson
Принадлежит: Individual

A method of making an aluminum airfoil includes brazing a first airfoil piece and a second airfoil piece together using a braze material that includes an element selected from magnesium and zinc, to form a braze joint between the first airfoil piece and the second airfoil piece. At least one of the first airfoil piece or the second airfoil piece has an aluminum alloy composition that includes greater than 0.8% by weight of zinc.

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Номер записи: 9
15-08-2013 дата публикации

Method of manufacturing an airfoil

Номер: US20130209262A1
Автор: Clifford C. Bampton, Daniel Edward Matejczyk, John R. Wooten
Принадлежит: Aerojet Rocketdyne of DE Inc, CalRAM Inc, United Technologies Corp

Disclosed is a method of manufacturing an airfoil. The method includes establishing an Argon (Ar)-free environment, providing a bed within the Argon free environment, providing a set of data instructions for manufacturing the airfoil, and providing a powdered Nickel (Ni)-based alloy on the bed. In one example, the powdered Nickel (Ni)-based alloy consists essentially of about 4.8 wt. % Iron (Fe), about 21 wt. % Chromium (Cr), about 8.6 wt. % Molybdenum (Mo), about 0.07 wt. % Titanium (Ti), about 0.40% Aluminum (Al), about 5.01 wt. % Niobium (Nb), about 0.03 wt. % Carbon (C), about 0.14 wt. % Silicon (Si), and a balance Nickel (Ni). The method further includes fusing the powdered Nickel (Ni)-based alloy with an electron beam with reference to the data instructions to form the airfoil.

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Номер записи: 10
24-10-2013 дата публикации

Fan impeller structure and manufacturing method thereof

Номер: US20130280086A1
Автор: Chu-hsien Chou
Принадлежит: Individual

A fan impeller structure and a manufacturing method thereof. The fan impeller structure includes a base seat, multiple blades and a ring member. Each blade has a main body made of plastic material and at least one fixing member made of metal material. The base seat and the ring member are made of metal material. The base seat and the ring member are respectively disposed on two sides of the blades. By means of the manufacturing method, the blades can be diversified and the universality of the blades is greatly increased to lower the manufacturing cost.

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Номер записи: 11
21-11-2013 дата публикации

Turbocompressor rotor and method for producing the same

Номер: US20130309098A1
Автор: Ralf Bode
Принадлежит: SIEMENS AG

A turbocompressor rotor for a turbocompressor for compressing process gas has a rotor body which makes contact with the process gas and which is produced entirely from a stainless steel material including 0.3 to 1.2% carbon and 12 to 19% chromium, wherein the steel material includes the alloy X39CrMo17-1.9. A process for producing such a turbocompressor rotor by casting includes manufacturing a casting model corresponding to the geometry of the rotor body by rapid technology and producing a casting mold using the casting model, or manufacturing a casting mold corresponding to the negative geometry of the rotor body by rapid technology, introducing the liquid steel material into the casting mold to form a cast workpiece as the rotor body, and finishing the turbocompressor rotor with the rotor body.

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Номер записи: 12
05-12-2013 дата публикации

Airfoil cover system

Номер: US20130319010A1
Автор: Kwan Hui, Michael A. Weisse
Принадлежит: Individual

An example airfoil for a gas turbine engine includes a body having a first surface extending from a first edge to a second edge and a cavity disposed in the body. A first cover is at least partially disposed within the cavity. The first cover includes a first portion cooperates with a corresponding second portion. A second cover covers the first cover and forms at least a portion of the first surface with the body. The first cover is disposed between the body and the second cover. The first cover and the second cover have a different coefficient of thermal expansion than the body.

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Номер записи: 13
05-12-2013 дата публикации

Impeller manufacturing method

Номер: US20130320073A1
Автор: Daisuke Kawada, Daisuke Tanaka, Hiroki Tagagi, Hiroshi Nakajima, Kazutoshi Yokoo, Koshiro Nihara, Yujiro Watanabe
Принадлежит: Mitsubishi Heavy Industries Ltd

The present invention relates to an impeller manufacturing method in which a thermal cycle is performed on an assembly body with a brazing material formed of a Ni-containing Au alloy being placed at a bond portion of at least two impeller constituent members. The thermal cycle includes a temperature increasing process with a temperature increasing rate of 20° C./hr. to 100° C./hr., the process including a first intermediate retention and a second intermediate retention each keeping the temperature, the first intermediate retention performed in a temperature range of 500° C. to 850° C. and the second intermediate retention performed in a temperature range of 850° C. to 950° C. (but not including 850° C.). In the thermal cycle, the temperature is increased in a temperature range exceeding 950° C. after the second intermediate retention at a rate lower than that before the second intermediate retention.

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Номер записи: 14
20-02-2014 дата публикации

Impeller, rotary machine including the same, and method for manufacturing impeller

Номер: US20140050585A1
Автор: Akihiro Nakaniwa, Daisuke Kawanishi
Принадлежит: Mitsubishi Heavy Industries Ltd

An impeller including: blades disposed in a circumferential direction of the impeller; a disk located close to a second end side of an axis of the impeller with respect to the blades, to which the blades are attached, and configured to be attached to a rotating shaft; and a shroud located close to a first end side of an axis of the impeller with respect to the blades, and to which the blades are attached. Flow passages are formed by the blades, the disk and the shroud. The blades, the shroud and a first portion of the disk close to the second end side of the axis of the impeller are integrated so as to form a first member. A second portion of the disk close to the first end side of the axis of the impeller forms a second member.

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Номер записи: 15
05-01-2017 дата публикации

VIBRATORY MASS MEDIA FIXTURE WITH TIP PROTECTOR

Номер: US20170001280A1
Автор: Beckman Micah, Masiukiewicz David K.
Принадлежит:

A fixture assembly includes a frame with a tip rail displaced from a main body. A method of polishing a gas turbine engine component includes restricting a flow of media adjacent to a tip of a component with an airfoil to be generally equal to a flow of media adjacent to a sidewall of the airfoil. 1. A fixture assembly for a vibratory mass media process , the assembly comprising:a frame with a tip rail displaced from a main body,wherein the tip rail is defined a predetermined distance from a tip of a component retained by the main body, andwherein the predetermined distance is about equal to a distance between each of a multiple of airfoils of the component.2. The assembly as recited in claim 1 , wherein the tip rail is arcuate.3. (canceled)4. The assembly as recited in claim 1 , further comprising a lock plate mountable to the main body to retain the component.5. The assembly as recited in claim 4 , wherein the component is a vane cluster with the multiple of airfoils.67-. (canceled)8. The assembly as recited in claim 1 , wherein the component is a vane cluster.9. A method of polishing a gas turbine engine component claim 1 , the method comprising:restricting a flow of media adjacent to a tip of a component with an airfoil to be generally equal to a flow of media adjacent to a sidewall of the airfoil; andlocating a tip rail predetermined distance from the tip of the airfoil,wherein the predetermined distance is about equal to a distance between each of a multiple of airfoils of the component.10. The method as recited in claim 9 , further comprising utilizing a Vibratory Mass Media (VMM) process for polishing of the gas turbine engine component.11. (canceled)12. The method as recited in claim 9 , further comprising removably mounting the component to a main body of a frame with the tip rail.13. The method as recited in claim 12 , further comprising enclosing a platform of the component.14. The method as recited in claim 13 , further comprising positioning the tip ...

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Номер записи: 16
05-01-2017 дата публикации

Method for adhering parts and device for implementing said method

Номер: US20170001366A1
Автор: Franck VARIN, Julien Schneider, Thierry Godon
Принадлежит: SNECMA SAS

A method is provided of bonding together at least two parts. The method includes assembling together at least two parts and at least one adhesive layer, the adhesive being configured so that its adhesive power increases on heating as a result of it polymerizing, at least one of the parts being made of composite material or of metal, the adhesive layer being present, after assembly, between the parts, the assembled together parts and the adhesive being present in a chamber defined by a wall, the wall having an inside face situated facing a first part present between the adhesive layer and the wall, the first part being intended to be bonded to a second part and only a fraction of the second part being present inside the chamber; and applying a liquid against the wall on its side opposite from the chamber.

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Номер записи: 17
04-01-2018 дата публикации

IMPELLER FOR ROTARY MACHINE, COMPRESSOR, SUPERCHARGER, AND METHOD FOR PRODUCING IMPELLER FOR ROTARY MACHINE

Номер: US20180002812A1
Автор: ARAI Takashi, MURONO Wataru, Torigoe Taiji, Watanabe Daigo, Yamada Masahiro, Yamaguchi Hideki
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

An impeller for a rotary machine includes: a base material of the impeller comprising Al or an Al alloy; a surface layer for the impeller formed by an electroless plating layer comprising a Ni—P based alloy; and an under layer disposed between the base material and the surface layer, the under layer having a smaller Vickers hardness than the surface layer. 116-. (canceled)17. An impeller for a rotary machine , comprising:a base material of the impeller comprising Al or an Al alloy;a surface layer for the impeller formed by an electroless plating layer comprising a Ni—P based alloy; andan under layer disposed between the base material and the surface layer, the under layer having a smaller Vickers hardness than the surface layer,wherein the surface layer has a P content rate of not less than 4 wt % and not more than 10 wt %.18. The impeller for a rotary machine according to claim 17 , wherein the surface layer has an amorphous structure.19. An impeller for a rotary machine claim 17 , comprising:a base material of the impeller comprising Al or an Al alloy;a surface layer for the impeller formed by an electroless plating layer comprising a Ni—P based alloy; andan under layer disposed between the base material and the surface layer, the under layer having a smaller Vickers hardness than the surface layer,wherein the under layer comprises a plating layer containing Ni.20. The impeller for a rotary machine according to claim 19 , wherein the plating layer serving as the under layer comprises a Ni—P based alloy having an amorphous structure claim 19 , the Ni—P based alloy having a P content rate of not less than 10 wt % and not more than 13 wt % in the under layer.21. The impeller for a rotary machine according to claim 19 , wherein the Ni plating layer serving as the under layer is an electrolytic plating layer having a Vickers hardness of not more than 350 HV.22. The impeller for a rotary machine according to claim 17 , wherein the under layer is a plating layer ...

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Номер записи: 18
04-01-2018 дата публикации

Centrifugal Fan

Номер: US20180003188A1
Автор: FUJIMOTO Seiya, Nara Kiyohisa
Принадлежит:

There is provided a centrifugal fan that effectively cools an electronic component with a simple structure. The centrifugal fan comprises an impeller having a plurality of pins extending in an axial direction, a rotor yoke formed with a plurality of through-holes through which the pins penetrate, the rotor yoke being joined to the impeller as the pins penetrate through the through-holes, and a circuit board arranged in a state having a gap with respect to the rotor yoke , wherein an end ′ of the pin protrudes from the rotor yoke to a side of the circuit board, and the plurality of pins are arranged with uneven pitch in a circumferential direction of the impeller. 1. A centrifugal fan comprising:an impeller having a plurality of pins extending in an axial direction;a rotor yoke formed with a plurality of through-holes through which the pins penetrate, the rotor yoke being joined to the impeller as the pins penetrate through the through-holes; anda circuit board arranged in a state having a gap with respect to the rotor yoke,whereinan end of the pin protrudes from the rotor yoke to a side of the circuit board, andthe plurality of pins are arranged with uneven pitch in a circumferential direction of the impeller.2. The centrifugal fan according to claim 1 , wherein an electronic component on the circuit board and a part of the pin protruding to the side of the circuit board are positioned to overlap with each other when viewed from a direction perpendicular to a rotation axis. This application claims the benefit of Japanese Patent Application No. 2016-130804, filed Jun. 30, 2016, which is hereby incorporated by reference in its entirety.The present invention relates to a centrifugal fan characterized by a function of cooling a built-in electronic component.Centrifugal fans have been widely used for purposes including cooling, ventilation, air conditioning of various equipment including home electrical equipment, OA equipment, and industrial equipment, or for air ...

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Номер записи: 19
04-01-2018 дата публикации

Variable pitch vane control ring bush retention foil and turbojet containing same

Номер: US20180003193A1
Автор: BAZOT Olivier, EDYNAK Jérémy Philippe Pierre
Принадлежит:

A flexible metal foil can be fixed on the inside part of a variable pitch vane control ring of a turbojet compressor, so as to close all through holes in which lever pins and their surrounding bushes are housed. As a result, the foil can retain the shank of the bush if the bush breaks. The use of such foil does not impose the development of a new model of control ring and its impact on the mass is small enough so that it does not affect engine performances. Therefore it avoids problems related to the breakage of bushes without having to make major changes to the existing system. 1. A foil made from a flexible metal material and to be fixed to an inside surface of a vane control ring with variable pitch for a turbojet , said control ring comprising a plurality of through holes each with an internal radial opening on a side of the inside surface of the control ring and an external radial opening on a side of an outside surface of the control ring , in each of which a bush can be housed to hold a pin of a control lever of one of the vanes , through the external radial opening of the hole , the foil having a length along a longitudinal direction and a width along a direction orthogonal to said longitudinal direction that are adapted to close the internal radial opening of at least one through hole in the control ring , said foil length being longer than the developed length of a determined angular sector of the control ring in which at least one pad of the control ring is located , at the angular sector at which the foil is to be fixed , and in which the foil contains an adapted hole to allow a pad support to pass through connecting the pad to the control ring , and wherein the foil adopts a determined shape in a section plane orthogonal to said longitudinal direction by which the foil can be fixed by click fitting onto the control ring at its inner surface.2. The foil according to claim 1 , comprising at least four folds along its longitudinal direction claim 1 , to ...

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Номер записи: 20
02-01-2020 дата публикации

VOLUMETRIC RESISTANCE BLOWERS

Номер: US20200003222A1
Автор: Cardenas Ruander, Kennedy David, MacDonald Mark, Raupp James
Принадлежит:

Volumetric resistance blowers are disclosed herein. An example volumetric resistance blower includes a housing, a motor, and a rotor disposed within the housing and rotated by the motor. The rotor is constructed of metal foam. 1. A volumetric resistance blower comprising:a housing;a motor; anda rotor disposed within the housing and rotated by the motor, the rotor constructed of metal foam.2. The volumetric resistance blower of claim 1 , wherein the rotor is constructed of nickel foam.3. The volumetric resistance blower of claim 1 , wherein the rotor is cylindrical or disc-shaped.4. The volumetric resistance blower of claim 1 , further including a hub claim 1 , the hub coupled to and driven by the motor claim 1 , the rotor coupled to the hub.5. The volumetric resistance blower of claim 4 , wherein the rotor is coupled to the hub via press fit.6. A volumetric resistance blower comprising:a motor;a carrier plate driven by the motor, the carrier plate including a plurality of posts; anda rotor coupled to the carrier plate via the posts, the rotor constructed of foam material.7. The volumetric resistance blower of claim 6 , wherein the rotor includes a plurality of openings claim 6 , and the posts extend into corresponding ones of the openings to couple the rotor to the carrier plate.8. The volumetric resistance blower of claim 7 , wherein the openings are smaller than the respective posts claim 7 , such that the foam material expands onto the posts.9. The volumetric resistance blower of claim 6 , further including a hub claim 6 , the hub coupled to and driven by the motor claim 6 , the carrier plate coupled to the hub.10. The volumetric resistance blower of claim 9 , wherein the carrier plate includes an opening claim 9 , the hub and the motor disposed in the opening.11. The volumetric resistance blower of claim 10 , wherein the carrier plate is co-molded with the hub.12. The volumetric resistance blower of claim 9 , wherein the rotor is not coupled to the carrier plate ...

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Номер записи: 21
02-01-2020 дата публикации

Stepped leading edge fan blade

Номер: US20200003224A1
Автор: Darrin Walter NIEMIEC, James C. Muth, Patrick Todd WOODZICK, William J. Carlson
Принадлежит: Individual

A fan blade apparatus for use in a high-volume, low-speed fan wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The fan blade coupled to an electric motor configured to rotate in an intended direction wherein the leading portion of the fan blade is at the forefront of the rotation of the blade. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. The stepped configuration creates turbulent air flow when the electric motor rotates in the intended direction.

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Номер записи: 22
13-01-2022 дата публикации

Water Vapor Distillation Apparatus, Method and System

Номер: US20220008837A1
Автор: Bhat Prashant, Clapp Otis L., III Stanley B., Kamen Dean, Langenfeld Christopher C., LaRocque Ryan K., Schnellinger Andrew A., Smith
Принадлежит:

A fluid vapor distillation apparatus. The apparatus includes a source fluid input, and an evaporator condenser apparatus. The evaporator condenser apparatus includes a substantially cylindrical housing and a plurality of tubes in the housing. The source fluid input is fluidly connected to the evaporator condenser and the evaporator condenser transforms source fluid into steam and transforms compressed steam into product fluid. Also included in the fluid vapor distillation apparatus is a heat exchanger fluidly connected to the source fluid input and a product fluid output. The heat exchanger includes an outer tube and at least one inner tube. Also included in the fluid vapor distillation apparatus is a regenerative blower fluidly connected to the evaporator condenser. The regenerative blower compresses steam, and the compressed steam flows to the evaporative condenser where compressed steam is transformed into product fluid. 1. A distillation apparatus comprising:a source fluid input;an evaporator condenser apparatus;a heat exchanger fluidly connected to said source fluid input and a product fluid output; and an inlet port;', 'an outlet port;', 'a stripper plate positioned between said inlet port and said outlet port;', a shaft; and', 'at least one water fed bearing; and, 'a shaft assembly, wherein the shaft assembly comprising, an inner magnet;', 'an outer magnet; and', 'a drive motor., 'a motor configured to drive the shaft, the motor comprising], 'a compressor fluidly connected to said evaporator condenser comprising2. The apparatus of wherein the evaporator condenser apparatus comprising:a substantially cylindrical housing; anda plurality of tubes in said housing.3. The apparatus of wherein the heat exchanger fluidly connected to said source fluid input and a product fluid output claim 1 , said heat exchanger comprising:at least one outer tube; andat least one inner tube.4. The apparatus of wherein said inner magnet and said outer magnet are axially positioned ...

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Номер записи: 23
03-01-2019 дата публикации

LEADING EDGE SHIELD

Номер: US20190003312A1
Автор: "GUIVARCH Jeremy", BASSOT ALAIN JACQUES MICHEL, POUZADOUX Frederic Jean-Bernard, ROMERO Jean-Louis, RUF THIBAULT
Принадлежит: SAFRAN AIRCRAFT ENGINES

The invention relates to the field of turbomachine blades, and more specifically to a leading-edge shield () for a turbomachine blade (), said leading-edge shield () including a pressure-side wing () and a suction-side wing (). Each pressure-side wing () and suction-side wing () extends heightwise from a bottom edge () to a top edge () and lengthwise from the leading edge () to a rear edge (), and they are connected together via the leading edge (), and wherein the rear edge () of the suction-side wing () presents at least one shaped segment (S, S) that is shaped in such a manner that the length of the suction-side wing () within this segment is shorter than the length (l, l, l, l, l, l) of the suction-side wing () at each end of this segment (S, S). 1. A leading-edge shield for a turbomachine blade , said leading-edge shield comprising a pressure-side wing and a suction-side wing , each extending heightwise from a bottom edge to a top edge and lengthwise from the leading edge to a respective rear edge , and connected together via the leading edge , and wherein the rear edge of the suction-side wing presents at least one shaped segment that is shaped in such a manner that the length of the suction-side wing within this segment is shorter than the length of the suction-side wing at each end of this segment.232. The leading-edge shield () according to claim 1 , wherein the at least one shaped segment of the rear edge of the suction-side wing is closer to the top edge than to the bottom edge of the suction-side wing.3. The leading-edge shield according to claim 1 , wherein the length of the suction-side wing within the at least one shaped segment is at least 10% shorter than the length of the suction-side wing at each end of the at least one shaped segment.4. The leading-edge shield according to claim 3 , wherein the length of the suction-side wing within the at least one shaped segment is at least 15% shorter than the length of the suction-side wing at each end of the ...

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Номер записи: 24
07-01-2021 дата публикации

Centrifugal impeller and centrifugal fan comprising the same

Номер: US20210003143A1
Автор: Haiming XU
Принадлежит: Zhongshan Ebs Technology Co Ltd

A centrifugal impeller including a wheel cover, a wheel disc, and a plurality of blades disposed between the wheel cover and the wheel disc. The wheel cover and the wheel disc each includes a sheet metal, and the plurality of blades includes a composite material. The wheel cover includes an air inlet. The wheel disc includes a central part and a motor mounting base disposed on the central part. Every two adjacent blades form an air channel including an air outlet. The plurality of blades each includes a metal frame, and a plastic shell disposed on the metal frame. Two ends of the metal frame are connected to the wheel cover and the wheel disc, respectively. The metal frame is integrated with the plastic shell through injection molding. The plastic shell is wrapped around at least a part of the metal frame.

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Номер записи: 25
03-01-2019 дата публикации

INLET BLEED HEAT SYSTEM FOR USE IN A TURBINE ENGINE

Номер: US20190003387A1
Автор: KIPPEL Bradly Aaron, Merchant Laxmikant, Parmeshwar Naveen, Ponyavin Valery Ivanovich, Zhang Hua
Принадлежит:

An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly. The inlet bleed heat (IBH) system includes a feed pipe for delivering compressor discharge air. The feed pipe includes a plurality of orifices along at least a portion of a length of the feed pipe, and each orifice of the plurality of orifices extends through a wall of the feed pipe for allowing the compressor discharge air to exit the feed pipe. The system also includes a heat shielding component that extends across the feed pipe, wherein the heat shielding component is configured to reduce heat transfer between the feed pipe and the silencer assembly of the turbine engine. 1. An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly , the inlet bleed heat (IBH) system comprising:a feed pipe for delivering compressor discharge air, said feed pipe comprising a plurality of orifices along at least a portion of a length of said feed pipe, each orifice of said plurality of orifices extending through a wall of said feed pipe for allowing the compressor discharge air to exit said feed pipe; anda heat shielding component that extends across said feed pipe, said heat shielding component configured to reduce heat transfer between said feed pipe and the silencer assembly of the turbine engine.2. The IBH system in accordance with claim 1 , wherein said heat shielding component comprises an arcuate sheet component extending about a portion of said feed pipe claim 1 , and positioned between said feed pipe and the silencer assembly.3. The IBH system in accordance with claim 2 , wherein said arcuate sheet component comprises aluminum or stainless steel.4. The IBH system in accordance with claim 1 , wherein said heat shielding component comprises a layer of thermal insulating material extending about a portion of said feed pipe claim 1 , and positioned between said feed pipe and the silencer assembly.5. The IBH system in accordance with claim 4 , wherein ...

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Номер записи: 26
03-01-2019 дата публикации

CENTRIFUGAL FAN

Номер: US20190003485A1
Автор: FUJIMOTO Seiya, HATAHARA Satoshi, KADONO Yuki, MAKINO Yuya, Matsubara Masaaki, MURAHATA Hiroshi, Nara Kiyohisa, NOGAMIDA Wataru, SEKI Tetsuya, TSUZAKI Atsushi
Принадлежит:

A valve device for a cooling water system of a motor vehicle, with a housing including a first connection and a second connection for a first liquid circuit, and a third connection and a fourth connection for a second liquid circuit, wherein the first connection is permanently fluidically connected to the second connection, and with a valve unit including a movably mounted valve element with which a thermally activatable spring element is associated, and which opens a connection between the third connection and the fourth connection in a first end position and cuts off the connection in a second end position. The thermally activatable spring element is arranged in a chamber located between the first connection and the second connection, which is permanently cut off from the third and the fourth connection and which preloads the valve element in the direction of the second end position. 1. A centrifugal fan comprising:a resin upper casing,a resin lower casing,an impeller,a motor, anda circuit board,wherein the impeller, the motor and the circuit board are housed between the resin upper casing and the resin lower casing,ribs are formed at a bottom surface of the lower casing,the lower casing includes primary pins for fixing the circuit board to the lower casing, andthe primary pins are reinforced by the rib.2. The centrifugal fan according to claim 1 , wherein the ribs include primary ribs extending along a radial direction and secondary ribs extending along a circumferential direction claim 1 , andeach of the primary pins is provided in a standing manner at a part where the primary rib and the secondary rib intersect.3. The centrifugal fan according to claim 2 , wherein the lower casing includes a circular protruding part reinforced by the primary ribs claim 2 , anda hollow cylindrical bearing holder, rotatably holding a shaft, which is a rotating axis of the impeller, is held in the circular protruding part.4. The centrifugal fan according to claim 3 , wherein each ...

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Номер записи: 27
11-01-2018 дата публикации

STRUT ASSEMBLY FOR AN AIRCRAFT ENGINE

Номер: US20180010616A1
Автор: King Daniel Elmer, Roll Christopher Timothy, Seitzer Kenneth E.
Принадлежит:

A strut assembly for a gas turbine engine includes an outer structural case. The outer structural case includes a first mounting pad for mounting a first strut and a second mounting pad for mounting a second strut. The outer structural case further includes a case ligament extending between the first mounting pad and the second mounting pad in a substantially straight direction to reduce an amount of bending stress on the outer structural case. 1. A strut assembly for a gas turbine engine , the strut assembly comprising: a first mounting pad for mounting a first strut;', 'a second mounting pad for mounting a second strut; and', 'a case ligament extending between the first mounting pad and the second mounting pad, the case ligament extending in a substantially straight direction from the first mounting pad to the second mounting pad., 'an outer structural case comprising'}2. The strut assembly of claim 1 , wherein the first mounting pad claim 1 , the second mounting pad claim 1 , and the case ligament are each formed of a composite material.3. The strut assembly of claim 1 , wherein the case ligament is formed of a composite material claim 1 , wherein the composite material forming the case ligament includes a plurality of substantially aligned fibers.4. The strut assembly of claim 3 , wherein the plurality of substantially aligned fibers extend in a direction from the first mounting pad to the second mounting pad.5. The strut assembly of claim 1 , wherein the case ligament defines an inside surface claim 1 , wherein the outer structural case further comprises a plurality of wedge members positioned along the inside surface of the case ligament adjacent to the first mounting pad and adjacent to the second mounting pad.6. The strut assembly of claim 5 , wherein the plurality of wedge members are non-structural components.7. The strut assembly of claim 6 , wherein the plurality of wedge members are formed of a composite material claim 6 , wherein the case ligament is ...

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Номер записи: 28
11-01-2018 дата публикации

GAS TURBINE COMPRESSOR PASSIVE CLEARANCE CONTROL

Номер: US20180010617A1
Автор: Adaickalasamy James, Benson Kyle Eric, Black Kenneth Damon, Cao Khoa Dang, Casavant Matthew Stephen, Floyd Donald Earl, Hansen Christian Michael, Klingler Brett Darrick, McClelland Damian Anthony, Perkins Devin Patrick
Принадлежит:

A gas turbine engine is disclosed having a turbine, one or more hydrocarbon gas combustors, and a compressor. The compressor has a rotor assembly with one or more rotor blade rows extending radially outward from an inner wheel disk. The compressor also has a stator assembly with one or more stator vane rows extending radially inward from an inner casing and positioned between adjacent rotor blade rows. The inner casing extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy. 1. A compressor for a gas turbine , comprising:a rotor assembly comprising one or more rotor blade rows comprising circumferentially spaced-apart rotor blades, each rotor blade extending radially outward from an inner wheel disk;a stator assembly comprising one or more stator vane rows comprising circumferentially spaced-apart stator vanes extending radially inward from an inner casing, each stator vane row positioned between adjacent rotor blade rows, the inner casing extending circumferentially around the rotor assembly thereby forming a plurality of inner flow paths defined by the rotor blades cooperating with the stator vanes, the rotor blades exhibiting a hot running rotor tip clearance and a cold build rotor tip clearance; andwherein said inner casing comprises at least one low-alpha metal alloy.2. The compressor according to wherein the at least one low-alpha metal alloy exhibits a coefficient of thermal expansion in the range of about 12 microns/meter/degrees Kelvin or less.3. The compressor according to wherein the inner casing comprises a low-alpha metal alloy having an alpha less than the alpha of the rotor blades.4. The compressor according to wherein the at least one low-alpha metal alloy is selected from the group consisting of aluminum claim 1 , iron claim 1 , nickel claim 1 , titanium claim 1 , cobalt claim 1 , niobium claim 1 , iron claim 1 , carbon claim 1 , chromium or mixtures thereof.5. The compressor according to ...

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Номер записи: 29
10-01-2019 дата публикации

BLADE, ASSOCIATED FAN AND TURBOJET ENGINE

Номер: US20190010807A1
Автор: "GUIVARCH Jeremy", BASSOT ALAIN JACQUES MICHEL, POUZADOUX Frederic Jean-Bernard, ROMERO Jean-Louis, RUF THIBAULT
Принадлежит: SAFRAN AIRCRAFT ENGINES

A leading-edge shield () for a turbomachine blade () includes a pressure-side wing () and a suction-side wing (). Each of the wings () extends along a height (H) from a bottom edge () to a top edge () and along a length, from the leading edge to a respective rear edge, and are connected together over the leading edge. At least one of the wings from among the suction-side wing () and the pressure-side wing () presents a segment (S), adjacent to the top edge () and extending over at least 10% of the height (H), wherein the rear edge () slopes towards the top edge (). 1. A blade extending along a height from a blade root to a blade tip and comprising a blade body and a leading-edge shield assembled on the blade body , the blade body being made of anisotropic material , and the leading-edge shield with better point impact resistance than the anisotropic material of the blade body , said leading-edge shield including two wings , each extending along a height from a bottom edge to a top edge and along a length , from the leading edge to a respective rear edge , the wings being connected together over the leading edge , and at least one of the wings presenting a segment , adjacent to the top edge and extending over at least 6% of the height , the respective rear edge sloping towards the top edge in such a manner that an angle of intersection between a tangent to the top edge and a tangent to any point of the rear edge in said segment is less than 75° , the anisotropic material comprising at least one layer with a main strength direction that is substantially parallel to an inside surface of a wing adjacent to said segment and presenting an angle relative to said top edge that is between 75° and 105° and substantially greater than a maximum value for said angle of intersection in said segment.2. The blade according to claim 1 , wherein said angle of intersection is less than 60°.3. The blade according to claim 1 , wherein the leading edge shield is made of metal material.4. ...

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Номер записи: 30
10-01-2019 дата публикации

Magnetically levitated rotor and a rotary machine with such a rotor

Номер: US20190013747A1
Автор: Giampiero Foiera, Mathias Hoffmann, Natale Barletta, Reto Schöb, Thomas Eberle, Thomas Gempp
Принадлежит: Levitronix GmbH

A magnetically levitated rotor includes a magnetically effective core and a sheathing made of a thermoplastically processible fluoropolymer. The sheathing completely encloses the magnetically effective core. The magnetically effective core comprises at least one permanent magnet and each permanent magnet has a metallic coating for protection against acidic or chemically aggressive substances. A plastic coating is disposed between the metallic coating and the sheathing, and includes a polymer belonging to the family of parylenes.

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Номер записи: 31
03-02-2022 дата публикации

COMPOSITE AIRFOIL WITH METAL STRENGTH

Номер: US20220034331A1
Автор: Chandrasekar Sujana, Jain Nitesh, Kray Nicholas Joseph, Lin Wendy Wenling, Maripalli Ramkrishna
Принадлежит:

A laminated composite airfoil assembly includes a first lamina formed of a material including metal fibers, and at least a second lamina formed of a material including at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate including metal fibers, a substrate including carbon fibers, and combinations thereof. 1. A laminated composite airfoil assembly comprising:a first lamina formed of a material comprising metal fibers; and wherein the airfoil assembly comprises a plurality of laminae formed from materials including the first lamina and the second lamina, and', 'wherein a subset of laminae of the plurality of laminae are formed from material comprising carbon fibers, the airfoil assembly further comprising metal threads extending into the subset of laminae of the plurality of laminae., 'at least a second lamina formed of a material comprising at least one of metal fibers intermixed with carbon fibers, only metal fibers, only carbon fibers, a substrate comprising metal fibers, a substrate comprising carbon fibers, and combinations thereof,'}2. The airfoil assembly of claim 1 , wherein the material of the first lamina is a pre-preg material claim 1 , and wherein the material of the second lamina is a pre-preg material.3. The airfoil assembly of claim 2 , wherein the pre-preg material of the first lamina comprises the metal fibers oriented in a first direction and the pre-preg material of the second lamina comprises the carbon fibers oriented in a second direction.4. The airfoil assembly of claim 1 , wherein the carbon fibers are unidirectional carbon fibers oriented in a first direction and the metal fibers crisscross the carbon fibers in at least one of the first lamina and the second lamina.5. The airfoil assembly of claim 1 , wherein the metal threads extend into the subset of the plurality of laminae in a 2.5D configuration.6. The airfoil assembly of claim 1 , wherein the metal threads extend into the subset ...

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Номер записи: 32
18-01-2018 дата публикации

Method of Making Machine Component with Aluminum Alloy Under Temperature-Limited Forming Conditions

Номер: US20180015545A1
Автор: Fan Yajun, JENSEN JEFF A., YANG NAN
Принадлежит: CATERPILLAR INC.

A method of making a machine component includes extruding a supply of an aluminum alloy to produce an extrusion. The extrusion is formed under temperature-limited forming conditions of 275° C. or less to produce a blank. The blank is machined to at least one predetermined tolerance to produce the machine component. 1. A method of making a machine component , the method comprising:extruding a supply of an aluminum alloy to produce an extrusion;forming the extrusion under temperature-limited forming conditions of 275° C. or less to produce a blank;machining the blank to at least one predetermined tolerance to produce the machine component.2. The method of claim 1 , further comprising:producing the supply of the aluminum alloy via a rapid solidification process.3. The method of claim 2 , wherein the rapid solidification process comprises melt spinning.4. The method of claim 2 , wherein the rapid solidification process includes producing a ribbon of the aluminum alloy and chopping the ribbon of the aluminum alloy to form a plurality of flakes claim 2 , and wherein the plurality of flakes is extruded to produce the extrusion.5. The method of claim 1 , wherein the aluminum alloy includes aluminum and at least one strengthening metal.6. The method of claim 1 , wherein the aluminum alloy includes aluminum and up to 3.5 percent by weight of at least one element of a first group of elements claim 1 , the first group of elements consisting of Si claim 1 , Sc claim 1 , Ti claim 1 , V claim 1 , Cr claim 1 , Mn claim 1 , Fe claim 1 , Ni claim 1 , Cu claim 1 , Y claim 1 , Zr claim 1 , Mo claim 1 , Ce claim 1 , Nd claim 1 , Er claim 1 , Yb claim 1 , Ta claim 1 , W.7. The method of claim 6 , wherein the aluminum alloy includes between 3.5 percent and 9 percent by weight of at least one element of a second group of elements claim 6 , the second group of elements consisting of Ti and V.8. The method of claim 7 , wherein the aluminum alloy includes between 3.5 percent and 8.5 percent ...

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Номер записи: 33
19-01-2017 дата публикации

TITANIUM ALLOYS EXHIBITING RESISTANCE TO IMPACT OR SHOCK LOADING AND METHOD OF MAKING A PART THEREFROM

Номер: US20170016103A1
Автор: Garratt Paul, James Steven, Kosaka Yoji, Thomas Roger
Принадлежит:

Titanium alloys formed into a part or component used in applications where a key design criterion is the energy absorbed during deformation of the part when exposed to impact, explosive blast, and/or other forms of shock loading is described. The titanium alloys generally comprise a titanium base with added amounts of aluminum, an isomorphous beta stabilizing element such as vanadium, a eutectoid beta stabilizing element such as silicon and iron, and incidental impurities. The titanium alloys exhibit up to 70% or more improvement in ductility and up to a 16% improvement in ballistic impact resistance over a Ti-6Al-4V alloy, as well as absorbing up to 50% more energy than the Ti-6Al-4V alloy in Charpy impact tests. A method of forming a part that incorporates the titanium alloys and uses a combination of recycled materials and new materials is also described. 1. A titanium alloy having a titanium base with added amounts of aluminum , at least one isomorphous beta stabilizing element , at least one eutectoid beta stabilizing element , and incidental impurities , the titanium alloy comprising mechanical properties of:a yield strength between about 550 and about 850 MPa;an ultimate tensile strength that is between about 600 MPa and about 900 Mpa;{'sub': '50', 'a ballistic impact resistance that is greater than about 120 m/s at the Vballistic limit; and'}a machinability V15 turning benchmark that is above 125 m/min,wherein the titanium alloy exhibits a hot workability that is greater than the hot workability exhibited by a Ti-6Al-4V alloy under similar conditions.2. The titanium alloy of claim 1 , wherein the titanium alloy further exhibitsa percent elongation that is between about 19% and about 40%; anda flow stress that is less than about 200 MPa measured at 1/sec and 800° C.3. The titanium alloy according to claim 1 , wherein the titanium alloy comprises:aluminum in an amount ranging between about 0.5 wt. % to about 1.6 wt. %;vanadium in an amount ranging between ...

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Номер записи: 34
19-01-2017 дата публикации

METHOD FOR COATING COMPRESSOR BLADE TIPS

Номер: US20170016454A1
Автор: Guo Changsheng, Strock Christopher W.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A method for forming a component having an abrasive portion includes forming the component and selectively forming a coating on the component using electric spark deposition to form the abrasive portion. A method for coating a blade tip with an abrasive material includes forming a blade having a tip and depositing a coating on the blade tip using electric spark deposition. A method includes providing a casing having an inner diameter surface, locating an abradable coating on a portion of the inner diameter surface, providing a blade configured to rotate within the casing and having a blade tip where the blade tip and the inner diameter surface of the casing form a seal, and depositing an abrasive coating on the blade tip using electric spark deposition so that the abrasive coating and abradable coating interact during rotation of the blade within the casing. 1. A method for forming a component having an abrasive portion , the method comprising:forming the component; andselectively forming a coating on the component using electric spark deposition to form the abrasive portion.2. The method of claim 1 , wherein the component is a blade claim 1 , and wherein the abrasive portion is located at a blade tip.3. The method of claim 1 , wherein the coating has a surface roughness (R) between about 1.25 micrometers (50 microinches) and about 5 micrometers (200 microinches).4. The method of claim 1 , wherein the coating has a thickness between about 0.025 millimeters (0.001 inches) and about 0.51 millimeters (0.020 inches).5. The method of claim 4 , wherein the coating has a thickness between about 0.10 millimeters (0.004 inches) and about 0.305 millimeters (0.012 inches).6. The method of claim 1 , wherein the coating is selected from the group consisting of alumina claim 1 , zirconia claim 1 , chromia claim 1 , hafnia claim 1 , ceria claim 1 , titania claim 1 , silica and combinations thereof.7. The method of claim 1 , wherein the coating is selected from the group consisting ...

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Номер записи: 35
18-01-2018 дата публикации

Clearance control between rotating and stationary structures

Номер: US20180017067A1
Автор: Louis R. Mouza, Philip R. Rioux
Принадлежит: United Technologies Corp

Aspects of the disclosure are directed to a system of an engine, comprising: a clearance control thermal ring, and a seal ring, where a radial gap with respect to an axial centerline of the engine is formed between a radial end of the clearance control thermal ring and a facing radial surface of the seal ring, where the clearance control thermal ring is made of a first material and the seal ring is made of a second material that is different from the first material, and where a first coefficient of thermal expansion of the first material is less than a second coefficient of thermal expansion of the second material.

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Номер записи: 36
18-01-2018 дата публикации

Gas injection blower

Номер: US20180017072A1
Автор: Jhih-Hao Jhang, Wu-Yu Fong, Zih-Ci Liou
Принадлежит: Orient Service Co Ltd

A gas injection blower includes a housing forming a box around the pump chamber, wherein the perimeter of the housing is also formed with a pump chamber communicating air inlet and an exhaust outlet, a fan shaft connected to a drive shaft the form of a rotatable type arranged in the pump chamber, the air inlet, forming a pressurized chamber of the pump flow passage between the fan and air vents and communicate with each other, the drive shaft extending through the shaft connected to a pump outdoor power source, wherein the drive shaft, at least between the inner wall of the frame around the blades and the pump chamber is formed a slit communicating the boost pressure drop of the flow channel, which is housing and forming a gap communicating the pressure drop gas injection passage; with the passage of gas injected into the inner injection cleaning gas pressure, to improve the traditional drop relatively easy accumulation of dust inside the gap problem.

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Номер записи: 37
18-01-2018 дата публикации

Fan blade cover system

Номер: US20180017085A1
Автор: Timothy E. Rivera
Принадлежит: Individual

A fan blade cover system that includes: a sleeve adapted to slide onto a fan blade; an opening at one end of the sleeve, where the opening enables the placement of the sleeve over the fan blade; and a fragrance embedded within the sleeve. The fan blade system creates a method of fan blade protection and room deodorizing that includes the steps of: configuring a sleeve for placement over a fan blade; embedding a fragrance embedded into the sleeve; and sliding the sleeve over the fan blade.

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Номер записи: 38
21-01-2021 дата публикации

FAN AND COVER FOR FAN

Номер: US20210018015A1
Автор: NIELS BUBKE
Принадлежит: ELEKTROSIL GMBH

A fan includes an electric motor and a fan wheel drivable or driven by the electric motor, arranged within its housing. The underside of the housing has an opening for an electric outlet, and a side the housing has a bracket, thereby forming a bushing. An electric line is arranged at least partially at the underside of the housing and is guided through the bushing, and a cover element is arranged at the underside of the housing. The cover element has a first section and a second section. The cover element is arranged at the underside of the housing in such a way that the first section is at least partially arranged in the bushing and clamps the electric line in the bushing while forming a strain relief, and that the second section covers the opening. 1. Fan having a housing , wherein in the housing an electric motor and a fan wheel drivable or driven by the electric motor are arranged , wherein on an underside of the housing , the housing has an opening for an electric outlet , wherein on a circumferential side the housing has a bracket , so that a bushing is formed between the bracket and the circumferential side , wherein an electric line is arranged at least partially at the underside of the housing and is guided through the bushing , characterized in that a cover element is arranged at the underside of the housing , wherein the cover element has a first section and a second section , wherein the first section and the second section are arranged at an angle towards each other , and in that the cover element is arranged at the underside of the housing in such a way that the first section is at least partially arranged in the bushing and clamps the electric line in the bushing while forming a strain relief , and in that the second section covers the opening.2. Fan according to claim 1 , characterized in that a duct is formed between the second section and the underside of the housing claim 1 , wherein the electric line is arranged in the duct claim 1 , and in that ...

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Номер записи: 39
18-01-2018 дата публикации

BLADE FOR A FAN

Номер: US20180019643A1
Автор: Brockschmidt Mario, Höhner Rene, Kocdemir Bora, Litinsky Alexander, Mashkin Andrey, Pohlmann Friedhelm, Schmidt Guido, Staubach Christian, Voss Simon
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

A blade for a fan that can be arranged on a rotor shaft of a rotor of a rotating electric machine, in particular a generator, wherein the blade is at least partially formed from a fiber composite material that has a polymer matrix with mineral fibers embedded therein. A method for producing a blade for a fan arrangeable on a rotor shaft of a rotor of a rotating electrical machine, in particular a generator, wherein the blade is produced using an injection molding method, and wherein a fiber composite material of a polymer matrix with mineral fibers embedded therein is used as injection molding material. 1. A blade for a fan arrangeable on a rotor shaft of a rotor of a rotating electrical machine , comprising:a fiber composite material which forms the blade at least in part,wherein the fiber composite material comprises a polymer matrix with mineral fibers embedded therein.2. The blade as claimed in claim 1 ,wherein the mineral fibers take the form at least in part of basalt fibers.3. The blade as claimed in claim 1 ,wherein the blade takes the form of a rotor blade or a guide vane.4. A fan for cooling a rotating electrical machine claim 1 , wherein the fan is arrangeable on a rotor shaft of a rotor of the rotating electrical machine claim 1 , the fan comprising:at least one blade ring arrangeable rotationally on the rotor shaft and formed of blades,{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'wherein the blades are configured according to .'}5. A method for producing a blade for a fan arrangeable on a rotor shaft of a rotor of a rotating electrical machine claim 1 , the method comprising:producing a blade using an injection molding method, andusing a fiber composite material comprising a polymer matrix with mineral fibers embedded therein as injection molding material.6. The method as claimed in claim 5 ,wherein the mineral fibers used are at least in part basalt fibers.7. The blade as claimed in claim 1 ,wherein the rotating electrical machine comprises a ...

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Номер записи: 40
28-01-2016 дата публикации

CENTRIFUGAL PUMP AND METHOD OF PRODUCING CENTRIFUGAL PUMP

Номер: US20160025098A1
Автор: NAKAGAWA Taiki, TAKEDA Tsuyoshi
Принадлежит:

A centrifugal pump includes a metallic main body casing in which a rotating blade member is accommodated. The metallic main body casing includes an upper main body casing, a lower main body casing which is fixed to the upper main body casing, and a blade casing, which partitions an interior space formed by the upper main body casing and the lower main body casing so that a fluid introducing passage is formed at an upper portion, and a rotating accommodating space that accommodates the rotating blade member is formed at a lower portion. An edge of the blade casing is airtightly fixed to the upper main body casing or the lower main body casing. 1. A centrifugal pump comprising:a metallic main body casing in which a rotating blade member is accommodated, an upper main body casing,', 'a lower main body casing which is fixed to the upper main body casing, and, 'the metallic main body casing including;'}a blade casing, which partitions an interior space formed by the upper main body casing and the lower main body casing so thata fluid introducing passage is formed at an upper portion, anda rotating accommodating space that accommodates the rotating blade member is formed at a lower portion,wherein an edge of the blade casing is airtightly fixed to the upper main body casing or the lower main body casing.2. The centrifugal pump of claim 1 , wherein the edge of the blade casing is airtightly fixed by welding claim 1 , brazing or adhesion.3. The centrifugal pump of claim 2 , wherein on a vicinity of a fixing portion of at least one of the upper main body casing claim 2 , the blade casing claim 2 , and the lower main body casing claim 2 , a groove for flow stop which prevents the fixing material from flowing is formed.4. The centrifugal pump of claim 3 , wherein the groove for flow stop is formed by notching at least one of the upper main body casing claim 3 , the blade casing claim 3 , and the lower main body casing.5. The centrifugal pump of claim 3 , wherein the groove for ...

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Номер записи: 41
26-01-2017 дата публикации

ROTOR DISC AND ROTOR FOR A VACUUM PUMP

Номер: US20170023002A1
Автор: Engländer Heinrich
Принадлежит:

A rotor disc for a vacuum pump, in particular a turbo molecular pump, having an inner ring. The inner ring is connected to a plurality of blade elements extending radially outward. The inner ring has at least one expansion joint. For assembly, the inner ring can be surrounded by a retaining ring and arranged on a hollow cylindrical carrier element as applicable. 1. Rotor disc for a vacuum pump , in particular a turbomolecular pump , comprisingan inner ring anda plurality of blade elements extending radially outward and being connected with the inner ring,whereinthe inner ring has at least one expansion joint.2. Rotor disc of claim 1 , wherein the at least one expansion joint extends over the entire width of the inner ring claim 1 , the expansion joint preferably extending obliquely.3. Rotor disc of claim 1 , further comprising a plurality of expansion tubes are provided regularly distributed over the circumference of the inner ring.4. Rotor disc of claim 1 , wherein the blade elements are tapered at the blade base.5. Rotor disc of claim 4 , wherein claim 4 , for tapering claim 4 , the blade elements have a recess in an upper side and a lower side claim 4 , the recesses preferably being mirror-symmetric.6. Rotor for a vacuum pump claim 4 , in particular a turbomolecular pump claim 4 , comprising{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'a plurality of rotor discs of arranged in the longitudinal direction of the rotor.'}7. Rotor of claim 6 , further comprising at least one retaining ring surrounding the inner ring in order to fix the inner ring.8. Rotor of claim 7 , wherein at least one of the retaining rings surrounds the inner rings of two adjacent rotor discs.9. Rotor of claim 7 , wherein the retaining ring covers the taper provided at the blade base.10. Rotor of claim 7 , wherein the retaining rings contact the upper side and the lower side of the blade elements for the purpose of damping vibrations.11. Rotor of claim 7 , wherein the retaining rings ...

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Номер записи: 42
26-01-2017 дата публикации

FAN BLADE WITH COMPOSITE COVER AND STRUCTURAL FILLER

Номер: US20170023006A1
Автор: Roche Charles H.
Принадлежит:

A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening and at least one cavity for purposes of reducing the weight of the fan blade. The cover overlays the opening and includes a peripheral edge that is received in a slot defined by the body. The cavities are filled with a filler material that may form a permanent part of the fan blade. 1. A fan blade comprising:a body having a pressure side, a suction side adjoining the pressure side along a leading edge and a trailing edge, the pressure side, the body having a base and a distal tip;the suction side defining an opening communicating with one or more cavities, the opening having a perimeter;the body further defining a slot extending underneath all or part of the perimeter away from the opening and into the body;the body further including a lip extending inwardly toward the opening and terminating at the perimeter of the opening;a cover comprising fiber or resin and having a peripheral edge that may be received into the slot to help secure the cover to the body, thereby covering part or all of the one or more cavities, the cover having an inner surface configured to face the opening; anda filler material disposed within at least one of the one or more cavities.2. The fan blade of wherein the filler material is a structural material that forms a permanent part of the fan blade.3. The fan blade of wherein the cover contacts the structural material.4. The fan blade of wherein the cover is bonded to the structural material.5. The fan blade of wherein the structural material has an outer surface facing the cover and conforming to the inner surface of the cover to prevent inward distortion of the cover.6. A method for fabricating a fan blade of a turbofan gas turbine engine claim 2 , the method comprising:manufacturing a body including a pressure side and a suction side, the pressure ...

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Номер записи: 43
26-01-2017 дата публикации

FAN BLADE WITH INTEGRATED COMPOSITE FAN BLADE COVER

Номер: US20170023007A1
Автор: Roche Charles H.
Принадлежит:

A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side. The body also includes a leading edge, a trailing edge, a distal tip and a base that is coupled to a hub. The suction side of the body includes at least one cavity for purposes of reducing the weight of the fan blade. The at least one body is surrounded by a slot that extends outwardly away from the cavity. A lip that extends inwardly towards the body further defines the slot. A cover is provided that overlays the cavity and includes a peripheral edge that is received in the slot and that is at least partially covered by the lip for a robust connection between the fan blade body and the cavity cover. 1. A fan blade comprising:a body including a pressure side and a suction side, the pressure and suction sides being disposed between and connected to a leading edge and a trailing edge, the pressure side and suction side also being disposed between and connected to a base and a tip;the suction side including at least one cavity that extends through the suction side and towards the pressure side, the cavity being surrounded by a slot that extends outwardly away from the cavity and into the body, the body further including a lip that extends inwardly towards the cavity and that at least partially defines the slot;a cover that overlays the cavity and that includes a peripheral edge that is received in the slot and that is at least partially covered by the lip.2. The fan blade of further including a coating disposed over the cover.3. The fan blade of wherein thicknesses of the coating and the lip are substantially equal.4. The fan blade of wherein the coating and the lip each include outer surfaces that are flush with each other.5. The fan blade of wherein the cavity includes a plurality of cavities that are surrounded by the slot.6. The fan blade of wherein the cavities are separated by walls that extend towards the suction side of the body.7 ...

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Номер записи: 44
26-01-2017 дата публикации

FAN BLADE WITH COMPOSITE COVER AND SACRIFICIAL FILLER

Номер: US20170023008A1
Автор: Roche Charles H.
Принадлежит:

A fan blade for a turbofan gas turbine engine is disclosed. The fan blade includes a body having a pressure side and a suction side and a cover. The suction side of the body includes an opening and at least one cavity for purposes of reducing the weight of the fan blade. The cover overlays the opening and includes a peripheral edge that is received in a slot defined by the body. The cavities are filled with a sacrificial material. 1. A fan blade comprising:a body having a pressure side, a suction side adjoining the pressure side along a leading edge and a trailing edge, the pressure side, the body having a base and a distal tip;the suction side defining an opening communicating with one or more cavities, the opening having a perimeter;the body further defining a slot extending underneath all or part of the perimeter away from the opening and into the body;the body further including a lip extending inwardly toward the opening and terminating at the perimeter of the opening;a semi-flexible cover comprising fiber or resin and having a peripheral edge that may be received into the slot to help secure the cover to the body, thereby covering part or all of the one or more cavities, the cover having an inner surface configured to face the opening; anda filler material disposed within at least one of the one or more cavities.2. The fan blade of wherein the filler material is a sacrificial material that can decompose claim 1 , ablate or otherwise diminish in size or weight.3. The fan blade of wherein the filler material has a density less than that of the fan blade body.4. The fan blade of wherein:the cover is made of a low temperature resin having a curing temperature; andthe sacrificial material has a melting point lower than the curing temperature.5. The fan blade of further comprising a flow path configured to allow the sacrificial material to escape from within the body.6. The fan blade of wherein;the body defines at least one root opening at the fan blade base and at ...

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Номер записи: 45
26-01-2017 дата публикации

FAN BLADE WITH SEGMENTED FAN BLADE COVER

Номер: US20170023009A1
Автор: Roche Charles H.
Принадлежит:

A lightweight fan blade for use in turbofan gas turbine engines is disclosed. The fan blade includes a metallic body having a pressure side and a suction side. The suction side of the body includes one or more cavities. A cover is then attached to the suction side of the body to cover or enclose the one or more cavities. The cover includes one or more transverse weakened areas, such as a transverse slit so that the cover separates into one or more smaller segments in the event of a foreign object damage (FOD) or fan blade out (FBO) event occurs. The smaller segments of the cover are less likely to do damage to downstream components such as the low and high-pressure compressors. A single smaller segment of the cover may allow for continued operation of the engine because the imbalance created by the event may be tolerated by the engine. 1. A fan blade comprising:a body including a pressure side and a suction side;the suction side including at least one cavity;a cover that overlays the cavity and that is adhered to the body; andthe cover including at least one transverse slit that divides the cover into a plurality of segments.2. The fan blade of wherein the transverse slit is located on the cover to control a size of the segment that is liberated from the fan blade as a result of a foreign object damage (FOD) event.3. The fan blade of further including a coating disposed over the cover.4. The fan blade of wherein the cavity includes a plurality of cavities.5. The fan blade of wherein the cavities are separated by walls that extend towards the suction side of the body.6. The fan blade of wherein walls each terminate at an outer edge that engages an underside of the cover.7. The fan blade of wherein the cavity accommodates a filler material.8. The fan blade of wherein the cavity is filled with a sacrificial material that decomposes when exposed to heat or a caustic agent.9. The fan blade of wherein the cover is fabricated from fibers and resin.10. The fan blade of ...

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Номер записи: 46
26-01-2017 дата публикации

FAN BLADE WITH ADHESIVE FABRIC STACKUP

Номер: US20170023010A1
Автор: Bergethon Richard B., Drozdenko Lee, Gates Brandon A., Hansen James O., Kirejczyk Maria C., Meyer Jesse C., Webb Scot A.
Принадлежит:

A blade comprises an airfoil extending from a trailing edge to a leading edge. The airfoil includes a body formed of an aluminum containing material. A sheath is at the leading edge and is formed of a titanium containing material. A sandwich is positioned intermediate the sheath and the airfoil body, the sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body. A gas turbine engine is also disclosed. 1. A blade comprising:an airfoil extending from a trailing edge to a leading edge, said airfoil including a body formed of an aluminum containing material; anda sheath at said leading edge and formed of a titanium containing material, with a sandwich positioned intermediate said sheath and said airfoil body, said sandwich including an outer adhesive layer adjacent the sheath, an intermediate fabric layer and an inner adhesive layer adjacent the body.2. The blade as set forth in claim 1 , wherein said fabric layer is a woven fabric layer.3. The blade as set forth in claim 2 , wherein said woven fabric layer is a fiberglass fabric.4. The blade as set forth in claim 3 , wherein said woven fabric layer has holes that are less than 0.0001 inch on average.5. The blade as set forth in claim 4 , wherein said woven fabric layer is between 0.005 and 0.010 inch in thickness.6. The blade as set forth in claim 2 , wherein said inner and outer adhesive layers are epoxy adhesives.7. The blade as set forth in claim 6 , wherein said inner and outer adhesive layers have an aerial weight of between 0.035 and 0.060 lb/sq ft.8. The blade as set forth in claim 2 , wherein said blade is a fan blade for a gas turbine engine.9. The blade as set forth in claim 1 , wherein said fabric layer has holes that are less than 0.0001 inch on average.10. The blade as set forth in claim 1 , wherein said fabric layer is between 0.005 and 0.010 inch in thickness.11. A gas turbine engine comprising:a fan rotor including a ...

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Номер записи: 47
24-01-2019 дата публикации

Thermal caulking device

Номер: US20190022954A1
Автор: Hiroshi Ishikawa, Naohiro Ohtsu, Satoshi Shiozaki, Shigeto Akahori, Yoshinori Tsurugai, Yuichi Tajiri
Принадлежит: Honda Motor Co Ltd

The first electrode section ( 7 a ) and the second electrode section ( 7 b ) are formed such that the outer portion connected to the upper portion of the heating section ( 6 ) is thinner than the inner portion connected to the lower portion of the heating section ( 6 ). The heating section ( 6 ) and the first electrode section ( 7 a ) are interconnected by an R-shaped first connecting portion ( 21 ). The inner circumferential sloping surface of the heating section ( 6 ) and the second electrode section ( 7 b ) are interconnected by an R-shaped second connecting portion ( 22 ). The first and second connecting portions ( 21 )( 22 ) are formed such that R becomes larger from the upper end to the lower end, where the upper portion is thin and the lower portion is thick. The thickness of an intermediate portion ( 6 b ) is smaller than the thicknesses of the first and second connecting portions ( 21 )( 22 ).

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Номер записи: 48
25-01-2018 дата публикации

TWIN CENTRIFUGAL SINGLE SPOOL ENGINE

Номер: US20180023576A1
Автор: Kashyap Tania Bhatia, Kupratis Daniel Bernard, Merry Brian D., Rugg Kevin L., Slavens Thomas N., Suciu Gabriel L., Utay Arthur W., Zelesky Mark F.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor. 1. A twin centrifugal compressor for an auxiliary power unit , comprising:a first airflow path at an input of the twin centrifugal compressor; anda second airflow path and a third airflow path defined by the twin centrifugal compressor, wherein the second airflow path and the third airflow path are split from the first airflow path.2. The twin centrifugal compressor of claim 1 , further including a blade claim 1 , wherein the blade comprises silicon nitride.3. The twin centrifugal compressor of claim 1 , wherein the second airflow path and the third airflow path are co-axial within the twin centrifugal compressor.4. The twin centrifugal compressor of claim 1 , wherein a pressure of the second airflow path is substantially the same as a pressure of the third airflow path.5. The twin centrifugal compressor of claim 1 , wherein a pressure ratio of at least one of the second airflow path or the third airflow path to the first airflow path is 7:1 or greater.6. The twin centrifugal compressor of claim 1 , further comprising a manifold defining a fourth airflow path claim 1 , wherein the fourth airflow path is comprised of a mix of the second airflow path and the third airflow path.7. A compressor section of an auxiliary power unit claim 1 , comprising:a forward centrifugal compressor; andan aft centrifugal compressor disposed aft of the forward centrifugal compressor.8. The compressor section of claim 8 , wherein the forward centrifugal compressor further comprises a blade. ...

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Номер записи: 49
25-01-2018 дата публикации

METHOD FOR IMPROVING TURBINE COMPRESSOR PERFORMANCE

Номер: US20180023591A1
Автор: Adjan Bachar
Принадлежит: Solar Turbines Incorporated

A method and device for retrofitting a gas turbine engine for improved hot day performance are disclosed. The method can include removing a first selected stator bladerow from the plurality of compressor stages, the first selected stator bladerow having a first inlet swirl angle and including a first plurality of fixed stator vanes. Each stator vane of the first plurality of fixed stator vanes can have a first stator vane angle. The method can also include providing a first improved stator bladerow to replace the first selected stator bladerow. The first improved stator bladerow can have a second plurality of fixed stator vanes, each having a second stator vane angle smaller than the first stator vane angle. The method can also include replacing the first selected stator bladerow with the first improved stator bladerow to produce an increased pressure ratio and flow rate compared to the first selected stator bladerow. 1. A method for retrofitting a gas turbine engine for improved hot day performance , the gas turbine engine having a plurality of compressor stages , each compressor stage of the plurality of compressor stages having a rotor bladerow and a stator bladerow , the method comprising:removing a first selected stator bladerow from the plurality of compressor stages, the first selected stator bladerow having a first inlet swirl angle and including a first plurality of fixed stator vanes, each stator vane of the first plurality of fixed stator vanes having a first stator vane angle referenced to a central axis of the gas turbine engine;providing a first improved stator bladerow to replace the first selected stator bladerow, the first improved stator bladerow having a second plurality of fixed stator vanes, each stator vane of the second plurality of fixed stator vanes having a second stator vane angle smaller than the first stator vane angle;installing the first improved stator bladerow in place of the first selected stator bladerow, the first improved stator ...

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Номер записи: 50
23-01-2020 дата публикации

Turbine airfoil with passive morphing structure

Номер: US20200024956A1
Автор: Narendra Digamber Joshi, Nicholas Joseph Kray, Paul Gerard Marsland, Samar Jyoti KALITA, Wayne Allen Spence
Принадлежит: General Electric Co

A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.

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Номер записи: 51
23-01-2020 дата публикации

FAN BLADE ASSEMBLY

Номер: US20200024978A1
Автор: Jaworowski Mark R., ZAFIRIS Georgios S.
Принадлежит:

The present disclosure relates generally to a fan blade assembly. In an embodiment, the fan blade assembly includes an airfoil having a forward edge covered by a sheath. The airfoil and the sheath are made from dissimilar conductive materials. A sacrificial anode layer is applied to at least a portion of the sheath so that the sacrificial anode layer will corrode instead of the airfoil. 1. A method of forming a fan blade assembly , comprising:providing a conductive airfoil;providing a conductive sheath including an outer surface;applying a sacrificial anode layer only on at least a portion of the outer surface of the sheath or only on a portion of the conductive airfoil, wherein the sacrificial anode layer is formulated as a colored composition or colored during application in order to provide a visual corrosion risk indicator;coating the sacrificial anode layer with an erosion protection coating, wherein when the sacrificial anode layer wears away the sacrificial anode layer provides a distinct visual indication;wherein the sacrificial anode layer is more anodic than the conductive airfoil; andwherein the conductive airfoil is joined to the sheath and the sacrificial anode layer corrodes instead of the conductive airfoil when a galvanic potential is created between the conductive airfoil and the sheath.2. The method of claim 1 , wherein the conductive sheath is joined to the conductive airfoil with a nonconductive adhesive.3. The method of claim 1 , wherein the conductive airfoil is formed from an aluminum alloy.4. The method of claim 1 , wherein the conductive sheath is formed from titanium or titanium alloys.5. The method of claim 1 , wherein:the conductive airfoil further includes an airfoil forward edge, a pressure side and a suction side;the conductive sheath further includes a sheath head section and first and second flanks extending from the sheath head section; andwherein the conductive sheath covers at least a portion of the airfoil forward edge, the first ...

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Номер записи: 52
23-01-2020 дата публикации

Method for manufacturing an annular casing equipping a turbomachine

Номер: US20200025017A1
Автор: Hubert Jean Marie FABRE, Marc-Emmanuel Jean Francois Techer, Pauline Nathalie Six
Принадлежит: Safran Aircraft Engines SAS

The invention relates to a method for manufacturing a carrying casing ( 12 ) provided with a collar ( 18 ) for supporting at least one cartridge of abradable material for a turbomachine, said carrying casing ( 12 ) comprising at least one bare annular casing ( 16 ) and one block of honeycomb material ( 20 ) that comprises an outer face ( 22 ) configured to be secured to an inner face ( 24 ) of said bare annular casing ( 16 ), said block being covered with a skin ( 26 ), characterized in that it comprises successively: —a step in which the outer face ( 22 ) of the block ( 20 ) is secured to the inner face ( 24 ) of the bare annular casing ( 16 ), —a step in which the circularity of San inner face ( 32 ) of the block ( 20 ) is monitored and in which, if necessary, the inner face ( 32 ) of the block ( 20 ) is machined to round, —a step in which, simultaneously, said skin ( 26 ) is produced and is secured to said block ( 20 ).

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Номер записи: 53
28-01-2021 дата публикации

Inlet bleed heat system for use in a turbine engine

Номер: US20210025326A1
Автор: Bradly Aaron Kippel, Hua Zhang, Laxmikant Merchant, Naveen Parmeshwar, Valery Ivanovich Ponyavin
Принадлежит: General Electric Co

An inlet bleed heat (IBH) system for use in a turbine engine including a silencer assembly. The inlet bleed heat (IBH) system includes a feed pipe for delivering compressor discharge air. The feed pipe includes a plurality of orifices along at least a portion of a length of the feed pipe, and each orifice of the plurality of orifices extends through a wall of the feed pipe for allowing the compressor discharge air to exit the feed pipe. The system also includes a heat shielding component that extends across the feed pipe, wherein the heat shielding component is configured to reduce heat transfer between the feed pipe and the silencer assembly of the turbine engine.

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Номер записи: 54
01-02-2018 дата публикации

Method for manufacturing impeller

Номер: US20180029273A1
Автор: Kosuke Ikeda, Ryoji Okabe, Yasunori Watanabe
Принадлежит: Mitsubishi Heavy Industries Ltd

The present invention prevents internal cracks occurring when an impeller molded using a fiber reinforced resin is manufactured by injection molding. This method for manufacturing an impeller is provided with: an injection step of filling a cavity with a molten resin containing reinforced fibers, from a gate side into which the molten resin flows, toward an opposite-gate side opposite to the gate side; and a dwell step of applying required pressure to the filled molten resin. In the injection step and the dwell step, directional cooling is performed with a temperature gradient such that the temperature becomes lower from the gate side toward the opposite-gate side. According to this method for manufacturing the impeller, the opposite-gate side shrinks with a decrease in the temperature of the molten resin since the temperature of the opposite-gate side is lower. Meanwhile, because the temperature on the gate side is increased, the molten resin can be replenished from the gate side so as to correspond to the amount of shrinkage on the opposite-gate side, and therefore the occurrence of internal tensile residual stress and cracks due to the shrinkage can be prevented.

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Номер записи: 55
02-02-2017 дата публикации

STEPPED-LOUVRE HEATING, VENTILATING AND AIR CONDITIONING UNIT USED IN HIGH-VELOCITY, LOW SPEED FAN

Номер: US20170030361A1
Автор: Buske Jeffrey William, Carlson William J., Muth James C., Niemiec Darrin Walter, Woodzick Patrick Todd
Принадлежит:

A manifold including a stepped louvre to control airflow along a fan blade. A fan blade for use in a high-volume, low-speed fan, wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. The fan distributes airflow from the manifold. 1. A high-volume , low-speed fan comprising:a fan blade mount affixed to an electromagnetic motor;a plurality of fan blades coupled to the fan blade mount having a length and width; andeach of the fan blades having a body portion, a leading edge portion and a trailing portion; wherein the leading edge portion of the fan blade is configured to include a plurality of steps extending along the length of the leading edge portion of each fan blade;a trapezoid-shaped diffuser to accommodate airflow from an HVAC duct having a plurality of openings, wherein the diffuser is positioned adjacent the electromagnetic motor and above the fan blades relative to the floor;a plurality of louvres positioned within the plurality of openings of the trapezoid-shaped diffuser, wherein the louvre is configured to include a plurality of steps extending along an edge portion of the louvre.2. The high-volume claim 1 , low-speed fan of claim 1 , wherein the length of each louvre step is substantially proportional to a total length of the edge of the louvre.3. The high-volume claim 1 , low-speed fan of claim 1 , wherein the width of the plurality of steps is substantially proportional to the overall width of the edge of the louvre.4. The high-volume claim 1 , low-speed fan of claim 1 , wherein the fan blade is configured to have a pitch of between 18° to 22°.5. The high-volume claim 1 , low-speed fan of claim 1 , wherein the steps are configured to create airflow of four miles per hour within 10-feet of a centerline of the fan at approximately 16 feet below the fan.6. The high-volume low-speed fan of claim 2 , ...

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Номер записи: 56
02-02-2017 дата публикации

Composite fan and method of manufacture

Номер: US20170030367A1
Автор: Charles Mark SHOGREN, Doug BURCHETT, Eric STRAUSS, Kevin CAHILL
Принадлежит: Horton Inc

A method of making a modular fan includes positioning a mounting pad of a blade between two plates of a center hub assembly, aligning the blade such that the mounting pad is located radially inward of an outer edge of at least one of the two plates, and spacing the outer edge of the at least one of the two plates from the blade at the outer edge.

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Номер записи: 57
02-02-2017 дата публикации

STEPPED LEADING EDGE FAN BLADE

Номер: US20170030369A1
Автор: Carlson William J., Muth James C., Niemiec Darrin Walter, Woodzick Patrick Todd
Принадлежит:

A fan blade for use in a high-volume, low-speed fan wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. 1. A high-volume , low-speed fan comprising:a fan blade mount affixed to the electromagnetic motor;a plurality of fan blades coupled to the fan blade mount having a length and width; andeach of the fan blades having a body portion, a leading edge portion and a trailing portion; wherein the leading edge portion of the fan blade is configured to include a plurality of steps extending along the length of the leading edge portion of each fan blade.2. The high-volume claim 1 , low-speed fan of claim 1 , wherein the length of each step is substantially proportional to a total length of the leading edge of the fan blade.3. The high-volume claim 1 , low speed fan of claim 1 , wherein the width of the plurality of steps is substantially proportional to the overall width of the leading edge of the fan blade.4. The high-volume claim 1 , low-speed fan of claim 1 , wherein the fan blade is configured to have a pitch of between 18° to 22°.5. The high-volume claim 1 , low-speed fan of claim 1 , wherein the steps are configured to create airflow of four miles per hour within 10-feet of a centerline of the fan at approximately 16 feet below the fan.6. The high-volume low-speed fan of claim 2 , wherein the width of the plurality of steps is substantially proportional to the overall width of the leading edge of the fan blade claim 2 , wherein each step decreases in width as the steps span at predetermined intervals from a centerline of the fan.7. The high-volume low-speed fan of claim 2 , wherein the steps being configured to create turbulent airflow.8. The high-volume low-speed fan of claim 2 , wherein there are at least three steps.9. The high-volume low-speed fan of claim 2 , wherein there are three steps claim 2 , the ...

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Номер записи: 58
01-02-2018 дата публикации

ARTICLE FOR HIGH TEMPERATURE SERVICE

Номер: US20180030839A1
Автор: Bewlay Bernard Patrick, Kulkarni Ambarish Jayant, Lesnicki Krzysztof Jacek, McCluskey Patrick James, Pritchard Byron Andrew, TIBBETTS Nicole Jessica
Принадлежит:

An article includes a substrate that is substantially opaque to visible light and a coating disposed on the substrate. The coating includes a coating material having an inherent index of refraction, wherein the coating has an effective index of refraction that is less than the inherent index of refraction, and wherein the effective index of refraction is less than 1.8. 1. An article , comprising:a substrate that is substantially opaque to visible light; anda coating disposed on the substrate, wherein the coating comprises a coating material having an inherent index of refraction, wherein the coating has an effective index of refraction that is less than the inherent index of refraction, and wherein the effective index of refraction is less than 1.8, and wherein the coating comprises a plurality of columnar structures oriented such that a longitudinal axis of a columnar structure forms an angle with respect to a direction tangential to the substrate that is less than 90 degrees.2. The article of claim 1 , wherein the substrate comprises a metallic material claim 1 , a ceramic material claim 1 , or an intermetallic material.3. The article of claim 1 , wherein the substrate comprises a titanium alloy claim 1 , a superalloy claim 1 , or a ceramic-matrix composite.4. The article of claim 1 , wherein the article comprises a component for a turbine assembly.5. The article of claim 4 , wherein the component is a compressor blade or compressor vane.6. The article of claim 1 , wherein the coating comprises a plurality of columnar structures oriented such that a longitudinal axis of a columnar structure forms an angle with respect to a direction tangential to the substrate that is less than 90 degrees.7. The article of claim 1 , wherein the angle is less than 80 degrees.8. The article of claim 1 , wherein the angle is less than 60 degrees.9. The article of claim 1 , wherein the plurality of columnar structures has a nominal intercolumnar spacing of less than about 5 ...

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Номер записи: 59
01-02-2018 дата публикации

FAN BLADE WITH COMPOSITE COVER

Номер: US20180030995A1
Автор: Weisse Michael A.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A fan blade includes a metallic body, a first composite cover, and a second composite cover. The metallic body may have a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, in accordance with various embodiments. The first and second retention slots may extend from the first side to the second side of the metallic body. The first composite cover may be coupled to the first side of the metallic body and may include a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body. The second composite cover may be coupled to the second side of the metallic body and may include a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body. 1. A fan blade comprising:a metallic body comprising a first side, a second side, a plurality of first retention slots, and a plurality of second retention slots, wherein the first and second retention slots extend from the first side to the second side of the metallic body;a first composite cover coupled to the first side of the metallic body, wherein the first composite cover comprises a plurality of first fingers that extend through the first retention slots and are coupled to the second side of the metallic body; anda second composite cover coupled to the second side of the metallic body, wherein the second composite cover comprises a plurality of second fingers that extend through the second retention slots and are coupled to the first side of the metallic body.2. The fan blade of claim 1 , wherein the metallic body is made from titanium.3. The fan blade of claim 1 , wherein the first and second composite covers are made from a graphite epoxy material.4. The fan blade of claim 1 , wherein the first composite cover is made from a first composite material and the second composite cover is made from a second composite material that is ...

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Номер записи: 60
01-02-2018 дата публикации

HEAT DISSIPATION MODULE

Номер: US20180030999A1
Автор: LEE Chiun-Peng, YANG Chaofu
Принадлежит:

A heat dissipation module is provided, including a frame, a base, and a fan. The frame has a depressed portion at an inner edge thereof. The base is connected to the frame and has a bottom surface. The fan is movably disposed on the base and has a plurality of blades. The end of an upper edge of the blades has a first height with respect to the bottom surface. The depressed portion has a second height with respect to the bottom surface, wherein the first height is less than the second height. 1. A heat dissipation module , comprising:a frame, having an outward expansion portion at an inner edge of the frame and adjacent to an air inlet of the heat dissipation module, wherein the outward expansion portion forms a depressed structure and has a curved surface or a sloping surface at the inner edge;a base, connected to the frame and having a bottom surface; anda fan, movably disposed on the base and rotatable with respect to the frame, wherein the fan has a plurality of blades, the end of an upper edge of each of the blades has a first height with respect to the bottom surface, and the outward expansion portion has a second height with respect to the bottom surface, wherein the first height is less than the second height.2. The heat dissipation module as claimed in claim 1 , wherein the end of the upper edge of each of the blades forms a curved structure.3. The heat dissipation module as claimed in claim 1 , wherein the upper edges of the blades are parallel to the bottom surface.4. The heat dissipation module as claimed in claim 1 , wherein the frame has a plurality of stationary vanes disposed on an air outlet of the frame and connected to the base claim 1 , a first angle is formed between the upper edges of the stationary vanes and the bottom surface claim 1 , and a second angle is formed between the lower edges of the stationary vanes and the bottom surface claim 1 , wherein the first angle and the second angle are acute angles.5. The heat dissipation module as ...

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Номер записи: 61
01-02-2018 дата публикации

MULTI-CELLULAR ABRADABLE LINER

Номер: US20180031000A1
Автор: Alban Cory, Lagow Benjamin
Принадлежит:

A seal runner adapted for use in a knife seal in a gas turbine engine is disclosed. The seal runner illustratively includes an abradable liner. 1. A method of making a seal runner for a gas turbine engine , the method comprisingsolidifying sequential layers of a feedstock to build up an integrated abradable liner,wherein the abradable liner extends at least partway around a central axis and has an integral set of abradable liner features that includes a web defining a plurality of cells and a first faceplate that defines a flat axial boundary of the abradable liner along substantially all of a forward or aft side of the abradable liner so that the first faceplate reduces windage pressure loss associated with interaction of gasses moving along or around the seal runner.2. The method of claim 1 , wherein the step of solidifying the feedstock is selected from the group consisting of powder bed fusion claim 1 , screen printing claim 1 , laser metal deposition claim 1 , and electron beam deposition.3. The method of claim 2 , wherein the feedstock is selected from the group consisting of a metal claim 2 , a ceramic claim 2 , a polymer claim 2 , and mixtures and combinations thereof.4. The method of claim 1 , wherein the abradable liner further includes a second faceplate spaced-apart from the first faceplate to locate the web therebetween claim 1 , the second faceplate defining another flat axial boundary of the abradable liner.5. The method of claim 4 , wherein each cell faces the central axis claim 4 , opens radially-inwardly claim 4 , and extends from a facing radially-outwardly side of the abradable liner towards a facing radially-inwardly side of the abradable liner.6. The method of claim 5 , wherein the web includes a plurality of web walls having an axial thickness that is substantially equal to an axial thickness of the first faceplate.7. The method of claim 6 , wherein portions of the first faceplate bound cells opening radially-inwardly of the web and no portion ...

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Номер записи: 62
01-02-2018 дата публикации

ANNULAR HEATSHIELD

Номер: US20180031002A1
Автор: Castle William R., Yuen Yuk-Kwan Brian
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A fan section includes a fan inlet case, fan bearing assembly, and an annular heatshield. The fan bearing assembly may be coupled to the fan inlet case and the annular heatshield may be mounted to the fan inlet case. In various embodiments, the annular heatshield is configured to reduce convective heat transfer from heated fluid to the fan bearing assembly. 1. A fan section comprising:a fan inlet case;a fan bearing assembly coupled to the fan inlet case; andan annular heatshield mounted to the fan inlet case, wherein the annular heatshield is configured to reduce convective heat transfer from heated fluid to the fan bearing assembly.2. The fan section of claim 1 , wherein the fan bearing assembly comprises a bearing and a bearing support engaged about the bearing claim 1 , wherein the annular heatshield is configured to reduce convective heat transfer from the heated fluid to the bearing support.3. The fan section of claim 2 , wherein:the annular heatshield is substantially parallel with a central rotational axis of the fan;the annular heatshield is radially outward relative to and spaced a radial distance apart from a radially outward surface of the bearing support that is parallel to the central rotational axis of the fan.4. The fan section of claim 2 , wherein an aft edge of the annular heatshield contours features of at least one of the bearing support and the fan inlet case.5. The fan section of claim 1 , wherein the annular heatshield comprises a nickel alloy material.6. The fan section of claim 1 , wherein the annular heatshield comprises a material configured to withstand temperatures up to and above a coking temperature of an oil configured for use in the fan bearing assembly.7. The fan section of claim 1 , wherein the annular heatshield and a radially inward surface of the fan inlet case form a plenum chamber for the heated fluid.8. The fan section of claim 7 , wherein the plenum chamber extends circumferentially around the fan bearing assembly.9. The fan ...

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Номер записи: 63
31-01-2019 дата публикации

OUTBOARD MOTOR

Номер: US20190031310A1
Автор: Matsui Takahiro, MORINO Makoto
Принадлежит:

An outboard motor includes an engine including a crankshaft, a generator including a rotor that rotates together with the rotation of the crankshaft and a stator in which a coil is wound so as to face the rotor, and a fan including a blade disposed coaxially with the rotor, provided separately from the rotor, and that rotates together with the rotation of the rotor. 1. An outboard motor comprising:an engine including a crankshaft;a generator including a rotor that rotates together with a rotation of the crankshaft and a stator in which a coil is wound so as to face the rotor; anda fan including a blade disposed coaxially with the rotor, provided separately from the rotor, and that rotates together with the rotation of the rotor.2. The outboard motor according to claim 1 , wherein the blade includes an annular first plate member and a plurality of fins that extend downward from the first plate member and are integral and unitary with the first plate member.3. The outboard motor according to claim 2 , wherein the plurality of fins extend in a radial direction and are arcuately curved in a planar view.4. The outboard motor according to claim 1 , whereinthe fan further includes a first air guide including a floor and a wall that extends upward from the floor and that surrounds fins provided on the blade from a lateral side; andan upper surface of the floor is disposed at a same or substantially a same height as a lower end of the blade.5. The outboard motor according to claim 4 , further comprising a cowling including an engine compartment in which the engine is housed; whereinthe fan further includes a lid-shaped second air guide that covers the first air guide from above between the cowling and the blade; andan upper surface of the blade that faces the lid-shaped second air guide is flat or substantially flat.6. The outboard motor according to claim 5 , further comprising an air guide passage through which air flows laterally from the blade and that extends along an ...

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Номер записи: 64
17-02-2022 дата публикации

SIDE-CHANNEL COMPRESSOR FOR A FUEL CELL SYSTEM FOR CONVEYING AND/OR COMPRESSING A GASEOUS MEDIUM

Номер: US20220049704A1
Автор: Kurz Michael
Принадлежит:

The invention relates to a side-channel compressor () for a fuel cell system () for conveying and/or compressing a gaseous medium, in particular hydrogen, comprising a housing (); a compressor chamber () which is situated in the housing () and which has at least one encircling side channel (); a compressor impeller () which is situated in the housing () and which is arranged so as to be rotatable about a rotational axis (), wherein the compressor impeller () has conveying cells () arranged on the impeller circumference in the region of the compressor chamber (); and in each case one gas inlet opening () formed on the housing () and one gas outlet opening (), which are fluidically connected together via the compressor chamber (), in particular the at least one side channel (). The housing () has a respective first and second end face () radially to the rotational axis (), each end face facing the compressor impeller (), and a first and second functionally relevant gap dimension () is formed in the region of each gap surface. According to the invention, the compressor impeller () is designed in multiple parts and has a first impeller shell () and a second impeller shell (). The impeller shells () are arranged adjacently to each other axially to the rotational axis () in particular, and each impeller shell is at least partly made of a plastic. 1137. A side-channel compressor () for a fuel cell system () for conveying and/or compressing a gaseous medium , the side-channel compressor comprising{'b': '3', 'a housing (),'}{'b': 30', '3', '19', '21, 'a compressor chamber (), which is situated in the housing () and which has at least one encircling side channel (, ),'}{'b': 2', '3', '4', '2', '5', '30, 'a compressor impeller (), which is situated in the housing () and which is arranged so as to be rotatable about an axis of rotation (), wherein the compressor impeller () has conveyor cells () arranged on a impeller circumference in a region of the compressor chamber (), and ...

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Номер записи: 65
17-02-2022 дата публикации

MULTI-STAGE TURBOMOLECULAR PUMP

Номер: US20220049705A1
Автор: Dowdeswell Stephen, Schofield Nigel Paul
Принадлежит:

A vacuum pump comprising a turbomolecular stage and a drag stage, the vacuum pump comprising a stator and a rotor. The rotor comprises a turbomolecular rotor and a drag rotor attached together. The turbomolecular rotor comprises a hub from which a plurality of blades extend, the hub comprising a mounting portion for mounting to a spindle of a motor and a hollow cylindrical portion, the hollow cylindrical portion extending from the mounting portion towards an outlet end of the turbomolecular stage. The drag rotor comprises a cylindrical skirt and an attachment part extending away from the cylindrical skirt, the attachment part extending within the hollow cylindrical portion of the hub of the turbomolecular rotor and being attached thereto at a point that is closer to the mounting portion than to the outlet end of the turbomolecular rotor. 11. A vacuum pump comprising a turbomolecular stage and a drag stage , said vacuum pump comprising a stator and a rotor , said rotor comprising a turbomolecular rotor and a drag rotor and a spindle of a motor; whereinsaid turbomolecular rotor comprises a hub from which a plurality of blades extend, said hub comprising a mounting portion for mounting to a member of said rotor and a hollow cylindrical portion, said hollow cylindrical portion extending from said mounting portion towards an outlet end of said turbomolecular stage; andsaid drag rotor comprises a cylindrical skirt and an attachment part extending away from said cylindrical skirt, said attachment part extending within said hollow cylindrical portion of said hub of said turbomolecular rotor and being attached to the member of said rotor at a point that is closer to said mounting portion than to said outlet end of said turbomolecular rotor.2. The vacuum pump according to claim 1 , wherein said drag rotor is formed of a material that is resistant to higher temperatures than a material forming said turbomolecular rotor.3. The vacuum pump according to claim 1 , wherein said ...

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Номер записи: 66
17-02-2022 дата публикации

FAN WITH LIGHT SOURCE

Номер: US20220049706A1
Автор: FAN Shao Dong, XIE Zubin
Принадлежит: COOLER MASTER TECHNOLOGY INC.

A fan including fan frame, fan rotor, at least one light source and first light guide component. Fan frame includes frame body and first assembling structures. Frame body includes outer and inner walls. First assembling structures each comprise extending base and post. Extending base protrudes from outer wall, a part of extending base is spaced apart from outer wall so that a gap is formed therebetween, and post protrudes from a side of extending base located away from outer wall. Light source is disposed on fan frame. First light guide component is engaged with fan frame. A light emitted from light source is configured to be incident on first light guide component. First light guide component includes first wall and second assembling structures. Second assembling structures are connected to first wall and respectively and removably mounted on first assembling structures. 1. A fan , comprising:a fan frame, comprising a frame body and a plurality of first assembling structures, wherein the frame body comprises an outer wall and an inner wall, the outer wall surrounds the inner wall, the inner wall forms an accommodation space, the plurality of first assembling structures each comprise an extending base and a post, in each of the plurality of first assembling structures, the extending base protrudes from the outer wall of the frame body, a part of the extending base is spaced apart from the outer wall of the frame body so that a gap is formed between the part of the extending base and the outer wall of the frame body, and the post protrudes from a side of the extending base that is located away from the outer wall of the frame body;a fan rotor, located in the accommodation space and rotatably disposed on the fan frame;at least one light source, disposed on the fan frame; anda first light guide component, engaged with the fan frame, wherein a light emitted from the at least one light source is configured to be incident on the first light guide component;wherein, the ...

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Номер записи: 67
30-01-2020 дата публикации

Casing arrangement for an axial compressor of a gas turbine engine

Номер: US20200032673A1
Автор: Oliver KÖHNE, Robert Kwiatkowski
Принадлежит: Rolls Royce Deutschland Ltd and Co KG

The invention relates to a casing assembly for an axial compressor of a gas turbine engine, wherein the casing assembly comprises a compressor casing which has a plurality of annular casings which in the axial direction are mutually contiguous by way of screwless interfaces and which are connected to one another by a clamping force. It is provided that the casing assembly comprises a clamping spring which provides the clamping force for connecting the annular casings, wherein the clamping spring is disposed and positioned in such a manner that said clamping spring is not part of a load path of the gas turbine.

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Номер записи: 68
09-02-2017 дата публикации

ELECTRIC COMPRESSOR AND METHOD FOR PRODUCING AN ELECTRIC COMPRESSOR

Номер: US20170037858A1
Автор: Back Wolfgang, Hofer Michael, SCHLAGER Gerd, Schmolzer Nicolai, Steinmair Gernot
Принадлежит:

An electric compressor for compressing a gas, particularly configured for use in a motor vehicle, comprising a control unit, an electric motor controlled by the control unit, a compressor wheel driven by the electric motor, and a housing at least partially surrounding the electric motor. The housing is produced by an encapsulation method such that a cooling structure is formed integrally with the housing, in particular within the housing, for ensuring cooling of the electric motor and of the control unit. A method for producing the electric compressor of this kind is also disclosed. 1. An electric compressor for compressing a gas and configured for use in a motor vehicle , the electric compressor comprising:a control unit;an electric motor, wherein the electric motor can be controlled by means of the control unit;a compressor wheel, wherein the compressor wheel can be driven by means of the electric motor; anda housing, wherein the housing at least partially surrounds the electric motor, wherein the housing is produced in such a way by means of an encapsulation method that a cooling structure is formed integrally with the housing, in particular in the housing, ensuring cooling of the electric motor and of the control unit.2. The electric compressor according to claim 1 , wherein the compressor wheel and the electric motor are arranged coaxially on a shaft.3. The electric compressor according to claim 1 , wherein the housing at least partially encloses the control unit.4. The electric compressor according to claim 1 , wherein the cooling structure has a plurality of cooling ducts.5. The electric compressor according to claim 4 , wherein the electric motor has a stator and the cooling structure is formed at least partially around the outer circumference of the stator.6. The electric compressor according to claim 5 , wherein the stator is of substantially annular design and has a plurality of axially extending recesses uniformly spaced apart along its outer ...

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Номер записи: 69
09-02-2017 дата публикации

COMPOSITE FAN

Номер: US20170037870A1
Автор: Burchett Doug, Cahill Kevin, Didandeh Hooshang, Shogren Charles Mark, Strauss Eric
Принадлежит:

A modular fan assembly includes a center hub assembly and a first blade attached to the center hub assembly. The center hub assembly includes a first plate having an outer edge, and a second plate having an outer edge. The first blade has a mounting pad and a working portion. The mounting pad is positioned in between the first plate and the second plate. The working portion extends beyond the outer edges of the first and second plates of the center hub assembly. A thickness of the first blade is smaller proximate the outer edge of the first plate than at the mounting pad to create a first gap between the first blade and the first plate at the outer edge of the first plate. 1. A modular fan assembly comprising: a first plate having an outer edge; and', 'a second plate having an outer edge; and, 'a center hub assembly comprisinga first blade attached to the center hub assembly, the first blade having a mounting pad and a working portion, wherein the mounting pad is positioned in between the first plate and the second plate, wherein the working portion extends beyond the outer edges of the first and second plates of the center hub assembly, and wherein a thickness of the first blade is smaller proximate the outer edge of the first plate than at the mounting pad to create a first gap between the first blade and the first plate at the outer edge of the first plate.2. The assembly of and further comprising:a plurality of additional blades, wherein the plurality of additional blades are each configured substantially identically to the first blade.3. The assembly of claim 1 , wherein the mounting pad has a planar configuration and a uniform thickness.4. The assembly of and further comprising:a second gap between the first blade and the second plate at the outer edge of the second plate.5. The assembly of claim 4 , wherein the first and second gaps are substantially equal.6. The assembly of claim 1 , wherein the first blade has a thickness profile from a root end to a tip ...

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Номер записи: 70
08-02-2018 дата публикации

Mistuned laminate airfoil

Номер: US20180038382A1
Автор: Larry Foster, Myron L. Klein
Принадлежит: United Technologies Corp

A gas turbine engine includes a fan mounting a first group of blades and a second group of blades. The first group of blades and the second group of blades share a profile shape. The first group of blades have a first laminate composition, and the second group of blades have a second laminate composition, distinct from the first laminate composition. A frequency of a vibratory mode of the first group of blades is offset from a frequency of a vibratory mode of the second group of blades.

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Номер записи: 71
08-02-2018 дата публикации

MICRO LATTICE HYBRID COMPOSITE FAN BLADE

Номер: US20180038385A1
Автор: Welch David A.
Принадлежит:

A fan blade includes a lattice structure, a fill, and a structural wrap. The lattice structure defines an airfoil body that has a cavity. The lattice structure defines at least one spar that extends radially from a root of the airfoil body towards a tip of the airfoil body. The fill is disposed within the cavity. The structural wrap is disposed about the lattice structure. The structural wrap defines a plurality of plies that extend from a leading edge of the airfoil body towards a trailing edge of the airfoil body. 1. A gas turbine engine , comprising: a lattice structure extending radially from a portion of a root towards a tip and extending axially from a leading edge towards a trailing edge, the lattice structure defining an airfoil body having a cavity, and', 'a structural wrap disposed about the airfoil body, the structural wrap extending radially from the portion of the root towards the tip and extending axially from the leading edge towards the trailing edge., 'a fan blade having2. The gas turbine engine of claim 1 , wherein the lattice structure is made of powdered metal material.3. The gas turbine engine of claim 1 , wherein the lattice structure is made of a powdered nonmetallic material.4. The gas turbine engine of claim 1 , wherein the lattice structure includes a first portion having a first thickness and a second portion having a second thickness greater than the first thickness.5. The gas turbine engine of claim 1 , wherein the fan blade includes a fill disposed within the cavity.6. The gas turbine engine of claim 5 , wherein the fill is at least one of a resin-based fill claim 5 , structural foam claim 5 , and a fiber-based fill.7. The gas turbine engine of claim 1 , wherein the root is made of a metallic material.8. The gas turbine engine of claim 7 , wherein the structural wrap is made of a composite material.9. A fan blade for a gas turbine engine claim 7 , comprising:a lattice structure defining an airfoil body having a cavity, the lattice ...

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Номер записи: 72
08-02-2018 дата публикации

FAN BLADE WITH COMPOSITE COVER

Номер: US20180038386A1
Автор: Foster Larry, Hertel Christopher J.
Принадлежит:

A fan blade assembly for a gas turbine engine includes a blade body, a blade cover secured to the blade body and an adhesive layer to secure the blade cover to the blade body, the adhesive layer configured to set at ambient temperature. A method of forming a fan blade assembly for a gas turbine engine includes forming a blade body, forming a blade cover separate from the blade body, and adhering the blade cover to the blade body via an adhesive layer located between the blade body and the blade cover, the adhesive layer configured to set at ambient temperature. 1. A fan blade assembly for a gas turbine engine , comprising:a blade body;a blade cover secured to the blade body; andan adhesive layer to secure the blade cover to the blade body, the adhesive layer configured to set at ambient temperature.2. The fan blade assembly of claim 1 , wherein the adhesive layer comprises a urethane claim 1 , silicone claim 1 , epoxy or polysulfide material.3. The fan blade assembly of claim 1 , wherein the blade cover and the blade body define one or more blade channels in the fan blade assembly.4. The fan blade assembly of claim 3 , wherein the blade body includes one or more ribs.5. The fan blade assembly of claim 3 , wherein the one or more blade channels extend in a substantially radial direction.6. The fan blade assembly of claim 1 , wherein the fan blade assembly is configured for an operating temperature between −65 and 200 degrees Fahrenheit.7. The fan blade assembly of claim 1 , wherein the blade body is formed from a first material and the blade cover is formed from a second material different from the first material.8. The fan blade assembly of claim 7 , wherein the blade body is formed from a metal material and the blade cover is formed from a carbon fiber reinforced composite material.9. A method of forming a fan blade assembly for a gas turbine engine claim 7 , comprising:forming a blade body;forming a blade cover separate from the blade body; andadhering the blade ...

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Номер записи: 73
24-02-2022 дата публикации

AERODYNAMIC ARM FOR AN AIRCRAFT TURBINE ENGINE CASING

Номер: US20220056804A1
Автор: MISSOUT Marc
Принадлежит: SAFRAN AIRCRAFT ENGINES

An aerodynamic arm for an aircraft turbine engine casing includes a tubular outer shell having a generally elongate shape extending substantially along an axis. The shell has axial ends configured to be connected to a turbine engine casing. An electrically conductive core extends inside the shell and has ends configured to electrically connect to the ends of the shell. An insulating material occupies a space between the core and the shell. 1. A casing aerodynamic arm for an aircraft turbine engine , comprising:an outer tubular shell having a generally elongated shape extending substantially along an axis (A-A), the shell comprising axial ends configured to connect to a casing of the turbine engine;an electrically conductive core extending inside the shell and having electrical connection ends at each of the ends of the shell; andan insulating material configured to occupy a space provided between the core and the shell, wherein for any cross-section of the aerodynamic arm in a plane perpendicular to the axis (A-A) of the shell, a maximum thickness (Ep) of the aerodynamic arm is between 2 mm and 10 mm, and a chord length (L) of the aerodynamic arm is between 30 mm and 150 mm.2. The aerodynamic arm according to claim 1 , wherein the insulating material has a minimum thickness (e) between 0.6 mm and 1.5 mm.3. The aerodynamic arm according to claim 1 , wherein a thickness of the core is between 1 mm and 5 mm.4. The aerodynamic arm according to claim 1 , wherein the ends of the core are configured to be connected to electrical conductors by one of mechanical connections and welds.5112a. The aerodynamic arm according to claim 1 , wherein each of the axial ends of the shell comprises a flange () configured to connect to the casing of the turbine engine.6. The aerodynamic arm according to claim 1 , wherein the insulating material is configured to withstand temperatures of up to 200° C. and is made from one of a liquid insulator and an organic insulating powder polymerised ...

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Номер записи: 74
24-02-2022 дата публикации

STEPPED LEADING EDGE FAN BLADE

Номер: US20220056923A1
Автор: Carlson William J., Muth James C., Niemiec Darrin Walter, Woodzick Patrick Todd
Принадлежит:

A fan blade apparatus for use in a high-volume, low-speed fan wherein the fan blade includes a body portion, a leading edge portion and a trailing portion. The fan blade coupled to an electric motor configured to rotate in an intended direction wherein the leading portion of the fan blade is at the forefront of the rotation of the blade. The leading edge portion of the fan blade includes a series of steps extending along the length of the leading edge. The stepped configuration creates turbulent air flow when the electric motor rotates in the intended direction. 1. A fan blade comprising:a body portion having a hub side, an exterior side, a top surface, and a leading edge portion measurable along a longitudinal edge of the fan blade;a tail portion measurable along a trailing edge portion of the fan blade;the body portion having a width measurable between the leading edge portion and the trailing edge portion;a leading edge forming a plurality of steps including at least a first step, a second step and a last step along a length of the leading edge wherein each of the plurality of steps decreases in a width edge of the fan blade between the leading edge and the trailing edge portion;the plurality of steps including a first air contact surface, a second air contact surface, and a last air contact surface, wherein the first air contact surface corresponds to the first step, the second air contact surface corresponds to the second step, and the last air contact surface corresponds to the last step and are aligned in a plane formed by a chord direction of the fan blade and a non-axial transverse direction of the fan blade; andthe plurality of steps are each configured to create a vortex.2. The fan blade of wherein each of the plurality of steps include a straight portion claim 1 , wherein at least a first step straight portion claim 1 , a second step straight portion claim 1 , and a last step straight portion are parallel to each other.3. The fan blade of claim 1 , ...

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Номер записи: 75
07-02-2019 дата публикации

Fan Assembly and Method

Номер: US20190040869A1
Автор: Adamski Stephen A., Buckley Michael F., Hall Craig R., Menoni Dominic Phillip, Shelby Richard R.
Принадлежит:

In one aspect, a fan assembly is provided that can be manufactured while producing a significantly reduced amount of scrap material. More specifically, the fan assembly utilizes a hub ring and one or more hub strips to support a plurality of blades rather than a solid center disc or end disc used by some prior approaches. In another aspect, a method is provided that includes bending a member into an annular configuration and joining end portions of the member together to rigidly fix the member in the annular configuration. The rigid annular member may be used as an end ring, a hub ring, an orifice, or other component, while producing significantly less scrap material than traditional approaches. 1. A method of manufacturing a fan assembly , the method comprising:bending an elongated, flat member having a pair of straight edges into an annular configuration wherein the edges are annular;joining end portions of the annular member together to rigidly fix the annular member in a flat, annular configuration;connecting the flat, annular member to end portions of a plurality of curved blades; andconnecting a hub support to the curved blades at a position spaced from the annular member along the curved blades.2. The method of further comprising forming openings in the flat claim 1 , annular member; andconnecting the flat, annular member to the end portions of the curved blades includes advancing portions of the curved blades into the openings of the flat, annular member.3. The method of wherein bending the elongated claim 1 , flat member into the annular configuration includes bending the elongated claim 1 , flat member so that one of the edges is a radially inner edge having a first radius and the other of the edges is a radially outer edge having a second radius lager than the first radius.4. The method of wherein the elongated claim 1 , flat member has a length claim 1 , a width perpendicular to the length defined between the edges claim 1 , and a thickness perpendicular ...

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Номер записи: 76
07-02-2019 дата публикации

Polymeric Compressor Wheel with Metal Sleeve

Номер: US20190040870A1
Автор: Allport John, Carter Jeffrey
Принадлежит: BORGWARNER INC.

A compressor wheel that can be employed in devices such as turbochargers. The compressor wheel includes an axially extending hub having an inlet end, a shaft bore extending from the inlet end and an arcuate outer surface opposed to the shaft bore. The axially extending hub is composed of a metal and has a porous region located proximate to the arcuate outer surface of the axially extending hub. The compressor wheel also includes a blade array disposed on the arcuate outer surface of the axially extending hub. The blade array has an outer surface and an inner region. The blade array comprises a plurality of circumferentially-spaced, radially and axially extending blades disposed thereon and is composed, at least in part of a polymeric material. Polymeric material located in the inner region of the blade array extends into the porous region defined in the axially extending hub. 110. A compressor wheel () comprising:{'b': 12', '18', '22', '18', '20', '34, 'an axially extending hub () having an inlet end (), a shaft bore () extending from the inlet end () and an arcuate outer surface () opposed to the shaft bore, the axially extending hub comprising a metal, the axially extending hub having at least one porous region, the porous region () located proximate to the arcuate outer surface of the axially extending hub;'}{'b': 24', '27', '29', '26, 'a blade array () disposed on the outer arcuate outer surface of the axially extending hub, the blade array having an outer surface () and an inner region (), the blade array comprising a plurality of circumferentially-spaced, radially and axially extending blades () disposed thereon, the blade array comprising at least in part, a polymeric material;'}wherein polymeric material that comprises the blade array extends into the porous region defined in the axially extending hub.2. The compressor wheel of wherein the polymeric material of the blade array comprises at least one of epoxy compounds claim 1 , phenolic polymers claim 1 , ...

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Номер записи: 77
06-02-2020 дата публикации

Casing Having a Non-Axisymmetric Composite Wall

Номер: US20200040909A1
Автор: Finn Scott Roger, Jain Manoj Kumar, Prabhakar Nagamohan Govinahalli
Принадлежит:

Walls of gas turbine engine casings, fan cases, and methods for forming walls, e.g., fan case walls, are provided. For example, a wall comprises a plurality of composite plies arranged in a ply layup. The wall is annular and circumferentially segmented into a plurality of regions that include at least one first region and at least one second region. The ply layup in the first and second regions is different such that the ply layup is non-axisymmetric. An exemplary fan case comprises an annular inner shell, a filler layer, an annular back sheet, and an annular outer layer. The back sheet is circumferentially segmented into a plurality of regions, including at least one first region and at least one second region, and comprises a plurality of composite plies arranged in a ply layup that is different in the first and second regions such that the ply layup is non-axisymmetric. 1. A wall of a gas turbine engine casing , comprising:a plurality of composite plies arranged in a ply layup,wherein the wall is annular and is circumferentially segmented into a plurality of regions, the plurality of regions including at least one first region and at least one second region, andwherein the ply layup in the at least one first region is different from the ply layup in the at least one second region such that the ply layup is non-axisymmetric.2. The wall of claim 1 , wherein the ply layup in the at least one first region is formed from a first plurality of plies claim 1 ,wherein the first plurality of plies comprises fibers oriented in a first direction and fibers oriented in a second direction.3. The wall of claim 2 , wherein the ply layup in the at least one second region is formed from the first plurality of plies and a second plurality of plies claim 2 ,wherein the second plurality of plies comprises fibers oriented in a third direction and fibers oriented in a fourth direction, the third and fourth directions being different from the first and second directions.4. The wall of ...

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Номер записи: 78
18-02-2016 дата публикации

Mounting arrangement for aerofoil body

Номер: US20160047257A1
Автор: Matthew Paul Jevons, Steven Aleksy Radomski
Принадлежит: Rolls Royce PLC

The present disclosure provides an aerofoil body comprising a root portion and a tip portion, each having a pressure surface and a suction surface. The pressure surface and suction surface of the root and/or tip portion each comprise a respective ridge portion. Each ridge portion has an inclined first face and an oppositely inclined second face. Each ridge portion may be, for example, a triangular or semi-circular prism.

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Номер записи: 79
16-02-2017 дата публикации

Single or multiple stage blower and nested volute(s) and/or impeller(s) therefor

Номер: US20170045056A1
Автор: Andrew Wilson, Barton John Kenyon, Ian Malcolm Smith, Nicholas Jerome Reed
Принадлежит: ResMed Motor Technologies Inc

A double-ended blower includes a blower motor assembly supporting opposed first and second shaft ends. The first and second shaft ends have respective first and second impellers attached thereto and enclosed within first and second volutes, respectively. The first volute is connected to an inlet and the second volute is connected to an outlet. The blower motor assembly is supported in a chassis enclosure and a radially outer inter-stage path is between the first and second volute. The second volute is at least partially substantially concentrically nested with the radially outer inter-stage gas path.

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Номер записи: 80
16-02-2017 дата публикации

Panel for lining a gas turbine engine fan casing

Номер: US20170045059A1
Автор: Ian C D Care, Stephen O OSIYEMI
Принадлежит: Rolls Royce PLC

A panel for lining a gas turbine engine fan casing includes a honeycomb core sandwiched between a backing skin and an outer skin. The backing skin is attached to an inner surface of the casing such that the outer skin forms a radially inward facing surface of a fan duct of the engine. The panel is joined along its sides to similar neighbouring panels such that, in use, the joined panels form a row of panels along the inner surface of the casing. The outer skin or the backing skin includes two face sheets bonded on top of each other, which are arranged such that their edges along each panel side that joins to a neighbouring panel are staggered in the direction of the row. The interfaces between the abutting face sheet edges are therefore correspondingly staggered in the direction of the row.

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Номер записи: 81
15-02-2018 дата публикации

FIBER COMPOSITE MATERIAL AND PREFORM AND FAN BLADE MADE THEREFROM

Номер: US20180045207A1
Автор: Paquin Bradley L.
Принадлежит:

A fiber composite material comprises a polymer matrix, carbon fibers, and non-carbon fibers, wherein the non-carbon fibers have a strain to failure value greater than the strain to failure value of the carbon fibers. Also discussed is a preform comprising the fiber composite material combined in a three dimensionally woven structure. Also discussed is a fan blade for a jet engine. 1. A fiber composite material comprising a polymer matrix , carbon fibers , and non-carbon fibers , wherein the non-carbon fibers have a strain to failure value greater than the strain to failure value of the carbon fibers.2. The fiber composite material of claim 1 , wherein the non-carbon fiber has a strain to failure value greater than 1.5%.3. The fiber composite material of claim 1 , wherein the carbon fiber has a diameter of 3 to 10 micrometers.4. The fiber composite material of claim 1 , wherein non-carbon fiber is present in an amount of 1 to 5 volume percent claim 1 , based on the total fiber volume in the fan blade.5. The fiber composite material of claim 1 , wherein the non-carbon fiber comprises aramid fibers claim 1 , hollow polypropylene fibers claim 1 , polyamide fibers claim 1 , polyester fibers claim 1 , or a combination comprising two or more of the foregoing.6. The fiber composite material of claim 1 , wherein the carbon fiber and the non-carbon fiber are combined in a woven fabric claim 1 , a uniweave claim 1 , or a three dimensionally woven structure.7. The fiber composite material of claim 1 , wherein polymer matrix comprises an epoxy.8. The fiber composite material of claim 1 , wherein polymer matrix comprises a polyimide.9. A preform comprising a polymer matrix claim 1 , carbon fibers claim 1 , and non-carbon fibers combined in a three dimensionally woven structure having yarns extending in the X claim 1 , Y and Z directions claim 1 , wherein the yarns extending in the Z direction comprise non-carbon fibers and the non-carbon fibers have a strain to failure value ...

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Номер записи: 82
15-02-2018 дата публикации

TORQUE TRANSMITTING KEY FOR ELECTRIC SUBMERSIBLE PUMPS

Номер: US20180045209A1
Автор: Johnson Keith Leon, NOWITZKI Wesley John
Принадлежит:

A torque transmitting key for electrical submersible pumps (ESP). An ESP system includes a rotatable shaft and a sleeve coupled to the rotatable shaft by an elongate key, the elongate key made of a carbide composite material, the carbide composite material including a carbide selected from the group consisting of tungsten carbide, titanium carbide and silicon carbide, and a composite material selected from the group consisting of cobalt, nickel and a combination of cobalt and nickel. An ESP system includes an elongate torque transmitting key, the elongate key coupling an ESP rotatable component to an ESP shaft such that the ESP rotatable component rotates with the ESP shaft, the elongate torque transmitting key seated in a keyway of the ESP rotatable component and a keyway of the ESP shaft, and the elongate torque transmitting key having a load optimizing cross-sectional shape. 1. An electric submersible pump (ESP) system comprising:a rotatable shaft extending longitudinally through at least one impeller and diffuser stage and at least one bearing set, each of the at least one bearing set comprising a sleeve and a bushing;the sleeve coupled to the rotatable shaft by an elongate key such that the sleeve rotates with the rotatable shaft; and a carbide selected from the group consisting of tungsten carbide, titanium carbide and silicon carbide; and', 'a composite material selected from the group consisting of cobalt, nickel and a combination of cobalt and nickel., 'the elongate key made of a carbide composite material, the carbide composite material comprising2. The ESP system of claim 1 , wherein the composite material comprises between 6% and 10% by mass of one of cobalt claim 1 , nickel or a combination thereof.3. The ESP system of claim 1 , wherein the elongate key has one of an arch or tee cross-sectional shape.4. The ESP system of claim 3 , wherein the elongate key has an arch cross-sectional shape and a rounded portion of the arch is seated in a keyway extending ...

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Номер записи: 83
15-02-2018 дата публикации

IMPELLER FOR ROTARY MACHINE, COMPRESSOR, SUPERCHARGER, AND METHOD FOR PRODUCING IMPELLER FOR ROTARY MACHINE

Номер: US20180045215A1
Автор: ARAI Takashi, INOUE Aki, Konno Yuya, MURONO Wataru, Torigoe Taiji, Watanabe Daigo, Yamaguchi Hideki
Принадлежит: MITSUBISHI HEAVY INDUSTRIES, LTD.

An impeller for a rotary machine includes: a base material of the impeller comprising Al or an Al alloy; and an electroless plating layer disposed so as to cover the base material, the electroless plating layer forming a surface layer of the impeller. The electroless plating layer comprises a Ni—P based alloy having an amorphous structure, the Ni—P based alloy having a P content rate of not less than 5 wt % and not more than 11 wt % in the electroless plating layer. 1. An impeller for a rotary machine , comprising:a base material of the impeller comprising Al or an Al alloy; andan electroless plating layer disposed so as to cover the base material, the electroless plating layer forming a surface layer of the impeller,wherein the electroless plating layer comprises a Ni—P based alloy having an amorphous structure, the Ni—P based alloy having a P content rate of not less than 5 wt % and not more than 11 wt % in the electroless plating layer.2. The impeller for a rotary machine according to claim 1 ,wherein the electroless plating layer has a layer thickness of not less than 15 μm and not more than 60 μm.3. The impeller for a rotary machine according to claim 1 ,wherein the electroless plating layer has a Vickers hardness of not less than 500 HV and not more than 700 HV.4. The impeller for a rotary machine according to claim 1 ,wherein a fracture ductility strain of the electroless plating layer is not less than 0.5%.5. The impeller for a rotary machine according to claim 1 ,wherein the impeller is a compressor impeller of a supercharger.6. A compressor comprising a compressor impeller which comprises the impeller according to .7. A supercharger claim 1 , comprising:{'claim-ref': {'@idref': 'CLM-00006', 'claim 6'}, 'the compressor according to ; and'}a turbine for driving the compressor.8. The supercharger according to claim 7 ,wherein the compressor is disposed in an intake passage of an internal combustion engine,wherein the turbine is configured to be driven by ...

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Номер записи: 84
15-02-2018 дата публикации

AIRFOIL SYSTEMS AND METHODS OF ASSEMBLY

Номер: US20180045216A1
Автор: Karlen Eric, Ursenbach Daniel O., Wentland William L.
Принадлежит:

An airfoil assembly includes an airfoil body extending from a root to a tip defining a longitudinal axis therebetween. The airfoil body includes a leading edge between the root and the tip. A sheath is direct deposited on the airfoil body. The sheath includes at least one metallic material layer conforming to a surface of the airfoil body. In accordance with another aspect, a method for assembling an airfoil assembly includes directly depositing a plurality of material layers on an airfoil body to form a sheath. In accordance with some embodiments, the method includes partially curing the airfoil body. 1. An airfoil assembly comprising:an airfoil body extending from a root to a tip defining a longitudinal axis therebetween, wherein the airfoil body includes a leading edge between the root and the tip; anda sheath direct deposited on the airfoil body, wherein the sheath includes at least one metallic material layer conforming to a surface of the airfoil body.2. An airfoil as recited in claim 1 , wherein the sheath is direct deposited on the leading edge of the airfoil body.3. An airfoil as recited in claim 1 , wherein the airfoil body includes a composite material.4. An airfoil as recited in claim 1 , wherein the sheath defines an internal pocket that includes a lattice structure.5. An airfoil as recited in claim 1 , wherein the sheath includes at least one of a composite or fiberglass structure bonded in between layers of the sheath.6. An airfoil as recited in claim 1 , wherein the sheath includes a plurality of layers.7. An airfoil as recited in claim 6 , wherein the layers are alternating material layers.8. An airfoil as recited in claim 6 , wherein an exterior layer includes a material of a higher erosion resistance than an interior layer.9. An airfoil as recited in claim 6 , wherein a first layer in direct contact with the airfoil body includes a material having a lower deposition temperature than layers exterior to the first layer.10. A method for assembling an ...

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Номер записи: 85
15-02-2018 дата публикации

SUPERPLASTIC FORMING

Номер: US20180045217A1
Автор: HALLIDAY Robert, WILKINSON Stephen J.
Принадлежит: ROLLS-ROYCE PLC

An aerofoil structure with a hollow cavity is manufactured by diffusion bonding and superplastic forming. Outer panels are formed of a first material; a membrane is formed of a second material. Stop-off material is applied to preselected areas on at least one side of the membrane or of one of the panels so as to prevent diffusion bonding between the panels and the membrane at the preselected areas. The panels and the membrane are arranged in a stack and a diffusion bonding process is performed to bond together the first and second panels and the membrane to form an assembly. A superplastic forming process is performed at a forming temperature to expand the assembly to form the aerofoil structure. The forming temperature is selected so that the second material undergoes superplastic deformation at the forming temperature and the first material does not undergo superplastic deformation at the forming temperature. 2. The method of claim 1 , in which the first material undergoes creep deformation at the forming temperature.3. The method of claim 1 , in which the superplastic temperature range of the first material is higher than the superplastic temperature range of the second material.4. The method of claim 1 , in which the first material is Ti-6Al-4V and the second material is ATI-425®.5. An aerofoil structure formed by diffusion bonding and superplastic forming claim 1 , the aerofoil structure comprising first and second outer panels formed of a first material and a membrane formed of a second material claim 1 , characterised in that the second material has undergone superplastic deformation and the first material has not undergone superplastic deformation.6. The aerofoil structure of claim 5 , in which the superplastic temperature range of the first material is higher than the superplastic temperature range of the second material.7. The aerofoil structure of claim 5 , in which the first material has undergone creep deformation. The present disclosure concerns ...

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Номер записи: 86
25-02-2016 дата публикации

INLET BELLMOUTH WITH COATING IN MEASUREMENT ANNULUS REGION

Номер: US20160053767A1
Автор: Morgan Rex Allen, Watts Stephen Ronald
Принадлежит:

An airflow inlet may include a bellmouth component having a substantially uneven internal surface, and a variable thickness coating in a measurement annulus region of the substantially uneven internal surface. The measurement annulus region includes only an annulus about the internal surface of the bellmouth component. The variable thickness coating is configured to present a more even internal surface than the substantially uneven internal surface. 1. An airflow inlet , comprising:a bellmouth component having a substantially uneven internal surface; anda variable thickness coating in a measurement annulus region of the substantially uneven internal surface, the variable thickness coating configured to present a more even internal surface than the substantially uneven internal surface,wherein the measurement annulus region includes only an annulus about the internal surface of the bellmouth component.2. The airflow inlet of claim 1 , wherein the coating includes an epoxy.3. The airflow inlet of claim 1 , wherein the coating includes a plastic.4. The airflow inlet of claim 1 , wherein the coating includes a fiberglass.5. The airflow inlet of claim 1 , further comprising a static pressure sensor system configured to determine a static pressure of an airflow through the bellmouth component using an annulus area based on the more even internal surface.6. The airflow inlet of claim 1 , wherein the bellmouth component includes a cast bellmouth component having the substantially uneven internal surface.7. The airflow inlet of claim 1 , wherein the substantially uneven internal surface varies up to 1.3 centimeters.8. The airflow inlet of claim 1 , wherein the measurement annulus region includes opposing slanted sides.9. The airflow inlet of claim 1 , wherein the annulus includes at least one strut at least partially covered with the variable thickness coating.10. A bellmouth component for an airflow inlet claim 1 , the bellmouth component comprising:a static pressure ...

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Номер записи: 87
25-02-2021 дата публикации

AIRFOIL SYSTEMS AND METHODS OF ASSEMBLY

Номер: US20210054750A1
Автор: Karlen Eric, Ursenbach Daniel O., Wentland William L.
Принадлежит:

An airfoil assembly includes an airfoil body extending from a root to a tip defining a longitudinal axis therebetween. The airfoil body includes a leading edge between the root and the tip. A sheath is direct deposited on the airfoil body. The sheath includes at least one metallic material layer conforming to a surface of the airfoil body. In accordance with another aspect, a method for assembling an airfoil assembly includes directly depositing a plurality of material layers on an airfoil body to form a sheath. In accordance with some embodiments, the method includes partially curing the airfoil body. 1. A method for assembling an airfoil assembly comprising:directly depositing at least one material layer on an airfoil body to form a sheath.2. A method as recited in claim 1 , further comprising partially curing the airfoil body.3. A method as recited in claim 1 , wherein the at least one material layer is one of a plurality of material layers claim 1 , the method further comprising ball milling at least one of the material layers prior to depositing an adjacent one of the material layers.4. A method as recited in claim 1 , wherein directly depositing the at least one material layer includes directly depositing at least one of material layers of alternating materials claim 1 , or groups of material layers of alternating materials.5. A method as recited in claim 1 , wherein the at least one material layer is one of a plurality of material layers claim 1 , the method further comprising bonding at least one of a composite or fiberglass structure between adjacent material layers of the sheath.6. A method as recited in claim 1 , wherein directly depositing the at least one material layer on the airfoil body includes depositing the material layer using a micro plasma spray process. This application is divisional application of U.S. patent application Ser. No. 15/235,291 filed Aug. 12, 2016, the contents of which are incorporated by reference herein in their entirety.The ...

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Номер записи: 88
25-02-2021 дата публикации

TURBOCHARGER IMPELLER

Номер: US20210054851A1
Автор: Iizuka Kuniaki, INOMATA Tatsumi, KIMACHI Kouta, OKADA Tomohisa, OZASA Takuya, Sasaki Yuji, YOSHIDA Takashi, YUMOTO Ryosuke
Принадлежит: IHI CORPORATION

A turbocharger impeller includes: a cylindrical boss portion disposed around a rotary axis; a hub portion connected to the boss portion and extends in a radial direction of the rotary axis; and a blade portion protruding from the boss portion and the hub portion toward a tip end side in the direction of the rotary axis and the radial direction. At least a part of an outer peripheral part of the hub portion in the radial direction or a part of the blade portion is provided with a resin second section and the second section is bonded to an aluminum first section. The turbocharger impeller includes the aluminum first section and the resin second section. 110.-. (canceled)11. A turbocharger impeller comprising:a cylindrical boss portion disposed around a rotary axis;a hub portion connected to the boss portion and extends in a radial direction of the rotary axis; anda blade portion protruding from the boss portion and the hub portion toward a tip end side in the direction of the rotary axis and the radial direction,wherein at least a part of an outer peripheral part of the hub portion in the radial direction or a part of the blade portion is provided with a resin second section and the second section is bonded to an aluminum first section,wherein a base part of the blade portion connected to the hub portion is formed as the first section and a part protruding from the base part of the blade portion is formed as the second section, andwherein the aluminum first section and the resin second section constitute the turbocharger impeller.12. The turbocharger impeller according to claim 11 ,wherein the second section is provided on an outer peripheral side of the first section.13. The turbocharger impeller according to claim 12 ,wherein the second section is provided on an outer peripheral side in relation to a predetermined radius and the first section is provided on an inner peripheral side in relation to the predetermined radius.14. The turbocharger impeller according to ...

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Номер записи: 89
25-02-2021 дата публикации

REINFORCED VACUUM SYSTEM COMPONENT

Номер: US20210054852A1
Автор: Horler Richard Glyn, Verma Mayank
Принадлежит:

The invention provides a rotor assembly for a vacuum pump. The rotor assembly comprises a hub and one or more rotor blade arrays each comprising at least one rotor blade, each rotor blade extending from a rotor blade root contiguous with the hub to a rotor blade tip, wherein each rotor blade comprises a continuous fibre reinforced matrix material. The invention further provides methods of designing and manufacturing rotor blades, and vacuum systems comprising a component comprising a continuous fibre reinforced matrix material. 1. A rotor assembly for a vacuum pump , the rotor assembly comprising a hub and one or more rotor blade arrays each comprising at least one rotor blade extending from a rotor blade root contiguous with the hub to a rotor blade tip , wherein the rotor blade comprises a continuous fibre reinforced matrix material and includes a continuous fibre that extends from said rotor blade to a portion of the hub immediately adjacent said rotor blade.2. The rotor assembly according to claim 1 , the rotor assembly being for a turbomolecular pump and comprising a substantially annular hub and one or more substantially annular rotor blade arrays each comprising a plurality of substantially identical rotor blades each rotor blade extending radially from a rotor blade root contiguous with the hub to a rotor blade tip claim 1 , wherein each rotor blade comprises a continuous fibre reinforced matrix material and a continuous fibre that extends from said rotor blade to a portion of the hub immediately adjacent said rotor blade.3. The rotor assembly according to comprising a plurality of rotor blade arrays.4. The rotor assembly according to wherein the rotor blade root and/or the rotor blade tip have a higher tensile strength and/or a higher flexural strength and/or higher creep resistance than the remainder of the blade.5. The rotor assembly according to wherein the hub and rotor blades comprise substantially similar or the same matrix material.6. The rotor ...

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Номер записи: 90
13-02-2020 дата публикации

Abrasive Tip Blade Manufacture Methods

Номер: US20200049020A1
Автор: Strock Christopher W.
Принадлежит: UNITED TECHNOLOGIES CORPORATION

A blade comprises an airfoil having a root end and a tip. A metallic substrate is along at least a portion of the airfoil. An abrasive tip coating comprises an abrasive and an aluminum-based matrix. An aluminum-based base layer is between the tip coating and the substrate. 1. A blade comprising:an airfoil having:a root end and a tip;a metallic substrate along at least a portion of the airfoil; andan abrasive tip coating comprising an abrasive and an aluminum-based matrix; andan aluminum-based base layer between the tip coating and the substrate.2. The blade of wherein the base layer is essentially free of the abrasive.3. The blade of wherein the aluminum-based matrix is essentially the same as the base layer.4. The blade of wherein:the matrix and the base layer are softer than the substrate.5. The blade of wherein:the matrix is galvanically sacrificial to the base layer and the substrate.6. The blade of wherein at least one of:the base layer is at least 30% softer than the substrate; andthe base layer has a yield strength at least 30% less than a yield strength of the substrate.7. The blade of wherein:the substrate is aluminum-based.9. The method of wherein the abrasive is a non-oxide abrasive.10. The method of wherein the base layer is sprayed to a thickness of 0.5 to 4.0 times a characteristic dimension of particles of the abrasive.11. The method of wherein the base layer is sprayed to a thickness of 13 micrometers to 0.90 millimeter.12. The method of wherein:the abrasive tip coating has a content of the abrasive of at least ten volume percent.13. The method of wherein:the matrix is at least 75 weight percent aluminum; andthe abrasive fills the matrix to at least 10 volume percent.14. The method of wherein:the tip coating has a characteristic thickness of 0.1 mm to 0.3 mm.15. The method of wherein:the abrasive has a characteristic size of 30 micrometers to 200 micrometers.16. The method of further comprising:applying a polymeric coating to a pressure side and a ...

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Номер записи: 91
13-02-2020 дата публикации

VARIABLE VANE DEVICES CONTAINING ROTATIONALLY-DRIVEN TRANSLATING VANE STRUCTURES AND METHODS FOR THE PRODUCTION THEREOF

Номер: US20200049163A1
Автор: Conner Richard David, Gentry Timothy, Hall Peter, Reynolds Bruce David
Принадлежит: HONEYWELL INTERNATIONAL INC.

Variable vane devices containing rotationally-driven translating vane structures are provided, as are methods for fabricating variable vane devices. In one embodiment, the variable vane device includes a flow assembly having a centerline, an annular flow passage extending through the flow assembly, cam mechanisms, and rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto. The translating vane structures include vane bodies positioned within the annular flow passage and angularly spaced about the centerline. During operation of the variable vane device, the cam mechanisms adjust translational positions of the vane bodies within the annular flow passage in conjunction with rotation of the translating vane structures relative to the flow assembly. By virtue of the translational movement of the translating vane structures, a reduction in the clearances between the vane bodies and neighboring flow assembly surfaces can be realized to reduce end gap leakage and boost device performance. 1. A variable vane device , comprising:a flow assembly having a centerline and an annular endwall partially bounding the flow passage;an annular flow passage extending through the flow assembly;rotationally-driven translating vane structures coupled to the flow assembly and rotatable relative thereto, the rotationally-driven translating vane structures having an angular Range of Motion (ROM) and including vane bodies positioned within the annular flow passage and angularly spaced about the centerline, wherein edge portions of the vane bodies are separated from the annular endwall by radial clearances; andcam mechanisms coupled to the flow assembly and to the rotationally-driven translating vane structures, the cam mechanisms adjusting translational positions of the vane bodies within the annular flow passage as the rotationally-driven translating vane structures rotate relative to the flow assembly, and such that an average value of the ...

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Номер записи: 92
22-02-2018 дата публикации

GAS-TURBINE ENGINE COMPOSITE COMPONENTS WITH INTEGRAL 3-D WOVEN OFF-AXIS REINFORCEMENT

Номер: US20180051705A1
Автор: Foster Larry, Naik Rajiv A., Riehl John D.
Принадлежит:

A gas turbine engine and a composite apparatus is disclosed. The gas turbine engine includes a composite apparatus body formed from a composite material, the composite material including a three dimensional preform, the three dimensional preform including a plurality of warp fibers disposed in a warp direction in a first plane, a plurality of fill fibers disposed in a fill direction, wherein the fill direction is perpendicular to the warp direction in the first plane, a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane, and a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction. 1. A fan blade comprising:a fan blade body formed from a composite material, the composite material including a plurality of warp fibers disposed in a warp direction in a first plane;', 'a plurality of filling fibers disposed in a fill direction, wherein the fill direction', 'is perpendicular to the warp direction in the first plane;', 'a plurality of z-yarn fibers disposed in a z-yarn direction, wherein the z-yarn direction intersects the warp direction through the first plane; and', 'a plurality of bias fibers disposed in a bias direction, wherein the bias direction is not aligned with the warp direction and the fill direction., 'a three dimensional preform, the three dimensional preform including2. The fan blade of claim 1 , wherein the bias direction is disposed in the first plane.3. The fan blade of claim 1 , wherein the fan blade body includes a root portion and an airfoil portion.4. The fan blade of claim 3 , wherein the root portion is thicker than the airfoil portion.5. The fan blade of claim 1 , wherein the fan blade body is formed from a plurality of composite layers.6. A gas turbine engine comprising: a plurality of warp fibers disposed in a warp direction in a first plane;', 'a plurality of filling ...

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Номер записи: 93
22-02-2018 дата публикации

Method of manufacturing supercharger

Номер: US20180051707A1
Автор: Hitomi Otsubo, Kazuhiko Inoguchi, Makoto Takeuchi, Masaya Hatanaka, Takashi Arai
Принадлежит: Mitsubishi Heavy Industries Ltd

An object is to provide a method of manufacturing a supercharger that can promptly and easily form an abradable layer in a supercharger. A method of manufacturing a supercharger is a method of manufacturing a supercharger including a turbine configured to rotationally drive, and a compressor having an impeller configured to rotate according to rotational force of the turbine and a housing ( 10 ) configured to store the impeller, and the method includes a process of applying coating of an abradable material which is to form an abradable layer ( 20 ) when being solidified, only to a predetermined range on a surface of the housing ( 10 ) via which the impeller and the housing ( 10 ) face.

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Номер записи: 94
26-02-2015 дата публикации

TURBOCHARGER

Номер: US20150056065A1
Автор: KANBARA Satoru, Maki Keijiro, Naruse Ryuji, TAKAMA Kenichiro
Принадлежит:

There is provided a turbocharger which can reduce whirl vibration. 1. A turbocharger comprising:a shaft connecting a turbine and a compressor;a bearing housing having a bearing portion turnably supporting the shaft; anda sliding bearing interposed between the shaft and the bearing portion,wherein the sliding bearing is disposed to be directly opposed to each of the shaft and the bearing portion,wherein the bearing portion is formed of an aluminum-based material,wherein the shaft is formed of a steel material, andwherein the sliding bearing is formed of a copper-based material.2. The turbocharger according to claim 1 ,wherein the bearing housing is divided into a turbine-side housing disposed at a turbine side and a compressor-side housing disposed at a compressor side,wherein the turbine-side housing is formed of stainless steel, andwherein the bearing portion is formed in the compressor-side housing.3. The turbocharger according to claim 2 , further comprisinga metal gasket interposed between the turbine-side housing and the compressor-side housing. The present invention relates to a technique of a turbocharger provided in an internal combustion engine.Conventionally, there has been publicly known a technique of a turbocharger provided in an internal combustion engine. Such a technique of a turbocharger is disclosed, for example, in Japanese Patent Application Laid-Open No. H9-310620.The turbocharger rotatably supports a shaft, by a bearing housing, connecting a turbine driven by exhaust gas and a compressor for compressing intake air. Further, the turbocharger includes a sliding bearing interposed between the bearing housing and the shaft, and is configured such that the shaft is rotated smoothly.However, in the case where the sliding bearing is used in a portion rotating at high speed like the shaft of the turbocharger, since clearances between the bearing housing and the sliding bearing and between the sliding bearing and the shaft are narrow, whirl vibration ...

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Номер записи: 95
23-02-2017 дата публикации

METHOD OF PROTECTING A COMPONENT OF A TURBOMACHINE FROM LIQUID DROPLETS EROSION, COMPONENT AND TURBOMACHINE

Номер: US20170051616A1
Автор: BELLACCI Michelangelo, Giannozzi Massimo, IOZZELLI Federico, MASI Gabriele
Принадлежит:

The method of protecting a component of a turbomachine from liquid droplets erosion provides covering at least one region of a component surface exposed to a flow of a fluid containing a liquid phase to be processed by the turbomachine with a protective layer. The protective layer consists of a plurality of adjacent sub-layers of different materials having high hardness in the range of 1000-3000 HV and low fracture toughness below 20 MPam. The materials are typically nitrides or carbides of titanium or aluminum or chromium or tungsten. In an embodiment, the covering is carried out by a PVD technique, in particular by Cathodic Arc PVD, or a CVD technique. The method may be applied to any component of turbomachines, but it may be particularly beneficial for parts of centrifugal compressors. 1. A method of protecting a component of a turbomachine from liquid droplets erosion , the method comprising:covering at least one region of a component surface exposed to a flow of a fluid containing a liquid phase to be processed by the turbomachine with a protective layer,wherein the protective layer comprises a plurality of adjacent sub-layers of two materials in alternate position,{'sup': '1/2', 'wherein the materials have high hardness in the range of 1000-3000 HV and low fracture toughness below 20 MPam, and'}wherein a first material of the two materials is a stoichiometric nitride or carbide or boride of titanium or zirconium or chromium or tungsten or aluminum or vanadium, and a second material of the two materials is a non-stoichiometric nitride or carbide or boride of titanium or zirconium or chromium or tungsten or aluminum or vanadium.2. The method of claim 1 , wherein the materials are Titanium Nitride (TiN).3. The method of claim 1 , wherein the covering is carried out by a CVD technique.4. The method of claim 1 , wherein the covering is carried out by a PVD technique.5. The method of claim 4 , wherein “targets” for the Cathodic Arc PVD are located and/or shaped so ...

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Номер записи: 96
23-02-2017 дата публикации

HIGH EFFICIENCY SELF-CONTAINED MODULAR TURBINE ENGINE POWER GENERATOR

Номер: US20170051667A1
Автор: Godman John
Принадлежит: Godman Energy Group, Inc.

A high efficiency self-contained modular turbine engine unit for generating power includes a housing defining an air intake and an exhaust port. A turbine engine is positioned and operable within the housing. The turbine engine includes a drive shaft a compressor rotor assembly, a compressor vane assembly, a combustor and diffuser assembly, a turbine vane assembly and a turbine rotor assembly. The combustor and diffuser assembly is a one-piece unit defining a shroud extending forwardly therefrom and a plurality of combustion flow channels extending rearwardly and radially inwardly thereby forming a flowpath angle in the range from about 15° to about 35° with the drive shaft. An igniter is positioned in each flow channel to ignite a fuel/oxygen mixture introduced into the compressor rotor assembly. External components required for operation of turbine engine are mounted within the housing. 1. A high efficiency self-contained modular turbine engine unit for generating power , the modular turbine engine unit comprising:a housing having a housing frame, a top panel, a bottom panel, a first side panel, a second side panel, a third side panel and a fourth side panel, each of the panels being removeably secured to the housing frame;an air intake defined in the housing; andan exhaust port defined in the housing; a drive shaft defining a drive shaft centerline,', 'at least one compressor rotor assembly mounted on the drive shaft,', 'at least one compressor vane assembly mounted on the drive shaft proximate to and downstream from the at least one compressor rotor assembly,', 'a combustor and diffuser assembly mounted on the drive shaft proximate to and downstream from the at least one compressor vane assembly, the combustor and diffuser assembly comprising a one-piece unit defining a shroud extending forwardly therefrom to define a flowpath for compressed air exiting the at least one compressor vane assembly, and a plurality of combustion flow channels extending rearwardly ...

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Номер записи: 97
10-03-2022 дата публикации

FAN FRAME

Номер: US20220074430A1
Автор: HSIEH Ming-Kai, LIU Geng-Hua, WU CHIH-HUI
Принадлежит:

A fan frame includes a metal base and a frame body. The metal base has a center portion, a plurality of supporting portions with strip shapes and a plurality of wing portions. Each of the supporting portions has a head end, a middle part and a tail end. The head end connects to a peripheral part of the center portion. The wing portions extend outwardly at an angle from the middle parts of the supporting portions, respectively. The frame body has a frame wall. The wing portions are partially at least covered by the frame body. Another fan frame is also disclosed. 1. A fan frame , comprising:a metal base having a center portion, a plurality of supporting portions with strip shapes and a plurality of wing portions, wherein each of the supporting portions has a head end, a middle part and a tail end, the head end connects to a peripheral part of the center portion, the wing portions extend outwardly at an angle from the middle parts of the supporting portions, respectively; anda frame body having a frame wall, wherein the wing portions are at least partially covered by the frame body.2. The fan frame according to claim 1 , wherein the angle is an obtuse angle.3. The fan frame according to claim 1 , wherein frame body is made of plastic.4. The fan frame according to claim 1 , wherein the wing portions are flat structures.5. The fan frame according to claim 1 , wherein the frame wall is made of metal claim 1 , the supporting portions radially extend from the frame wall inwardly and connect to the center portion.6. The fan frame according to claim 1 , wherein the center portion claim 1 , the supporting portions and the wing portions are integrally formed as one piece.7. The fan frame according to claim 1 , further comprising:a peripheral connection portion, wherein the peripheral connection portion is an annular structure, the tail ends of the supporting portions connect to the peripheral connection portion.8. The fan frame according to claim 7 , wherein the center portion ...

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Номер записи: 98
04-03-2021 дата публикации

Method of forming gas turbine engine components

Номер: US20210060692A1
Автор: Daniel A. Bales, Francis B. Parisi, Robert C. Dolan, Thomas DeMichael
Принадлежит: Raytheon Technologies Corp

A method of forming a gas turbine engine component according to an example of the present disclosure includes, among other things, attaching a cover skin to an airfoil body, the airfoil body and the cover skin cooperating to establish pressure and suction sides of an airfoil, positioning the airfoil between first and second dies of a deforming station, heating the airfoil body to a first predefined temperature threshold between the first and second dies, and moving the first die relative to the second die to hold the airfoil between the first and second dies subsequent to the heating step, and then deforming the airfoil between the first and second dies.

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Номер записи: 99
21-02-2019 дата публикации

Method for producing casing for radial compressor, and method for producing radial compressor

Номер: US20190055961A1
Автор: Kazutake FUJISAWA, Kenichiro Iwakiri, Ryoji Okabe, Tadashi KANZAKA, Takahiro Yamashita, Yasunori Watanabe
Принадлежит: Mitsubishi Heavy Industries Engine and Turbocharger Ltd

The present invention provides a method for producing a casing for a compressor, the method including an intake-side casing molding process of molding an intake portion and a first main body portion of a scroll portion by integral molding of resin; an impeller-side casing molding process of integrally molding a second main body portion of the scroll portion and a diffuser portion by a resin molding metal mold used in the intake-side casing molding process; a die sliding process of combining the intake portion and the first main body portion which have been integrally molded, and the second main body portion and the diffuser portion which have been integrally molded, by slide of the resin molding metal mold; and a secondary molding process of joining the intake portion and the first main body portion, and the second main body portion and the diffuser portion combined with each other by resin.

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Номер записи: 100