Настройки

Укажите год
-

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

Подробнее
-

Мониторинг СМИ

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

Подробнее

Форма поиска

Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Ведите корректный номера.
Укажите год
Укажите год
Применить Всего найдено 3. Отображено 3.
29-08-2013 дата публикации

COMBUSTION SYSTEM FOR A GAS TURBINE ENGINE AND METHOD FOR DIRECTING FUEL FLOW WITHIN THE SAME

Номер: US20130219911A1
Автор: Rodolphe Dudebout, Richard Bohman, Don Striker, Michael McPherson, Matt Greenman
Принадлежит: HONEYWELL INTERNATIONAL INC.

Disclosed is a combustion system for a gas turbine engine, which includes a combustor and a plurality of fuel injector nozzles within the combustor. The plurality of fuel injector nozzles include at least one start nozzle and at least of run nozzle, wherein each of the plurality of fuel injector nozzles is a single-circuit fuel injector nozzle. The combustion system further includes a fuel flow directing system to selectively deliver fuel flow to each of the at least one start nozzle and at least one run nozzle, wherein the fuel flow directing system is configured to deliver preferential flow of fuel to the at least one start nozzle during an engine start-up procedure and is further configured to deliver an equalized flow both of the at least one start nozzle and the at least one run nozzle as a total engine fuel flow is near or above an idle setting. 1. A combustion system for a gas turbine engine , comprising:a combustor;a plurality of fuel injector nozzles within the combustor, wherein the plurality of fuel injector nozzles comprise at least one start nozzle and at least of run nozzle, wherein each of the plurality of fuel injector nozzles is a single-circuit fuel injector nozzle; anda fuel flow directing system to selectively deliver fuel flow to each of the at least one start nozzle and at least one run nozzle, wherein the fuel flow directing system is configured to deliver preferential flow of fuel to the at least one start nozzle during an engine start-up procedure and is further configured to deliver an equalized flow both of the at least one start nozzle and the at least one run nozzle as a total engine fuel flow is near or above an idle setting.2. The combustion system of claim 1 , wherein the at least one start nozzle is located near an igniter3. The combustion system of claim 1 , comprising four start nozzles and twelve run nozzles.4. The combustion system of claim 1 , wherein the preferential flow of fuel is at or above a level sufficient for fuel ...

Подробнее
Номер записи: 1
17-05-2018 дата публикации

SCAVENGE METHODOLOGIES FOR TURBINE ENGINE PARTICLE SEPARATION CONCEPTS

Номер: US20180135516A1
Автор: Shakeel Nasir, Yogendra Yogi Sheoran, John Schugardt, Daniel Aukland, Mahmoud Mansour, Cristopher Frost, Matt Greenman
Принадлежит: HONEYWELL INTERNATIONAL INC.

A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation. 1. A method for scavenging small particles from a turbine engine , the method comprising the steps of:compressing air in a compressor that rotates about a longitudinal axis to generate compressed air, wherein the compressed air that exits the compressor includes at least a tangential flow component and a radial flow component, and wherein the compressed air comprises a plurality of small particles;directing the compressed air through a flowpath, downstream of the compressor, which causes a reduction in the radial flow component and the introduction of or an increase in an axial flow component;removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path;returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum; andremoving the majority of the small particles from the ...

Подробнее
Номер записи: 2
13-02-2020 дата публикации

SCAVENGE METHODOLOGIES FOR TURBINE ENGINE PARTICLE SEPARATION CONCEPTS

Номер: US20200049069A1
Автор: Shakeel Nasir, Yogendra Yogi Sheoran, John Schugardt, Daniel Aukland, Mahmoud Mansour, Cristopher Frost, Matt Greenman, NASIR SHAKEEL, SHEORAN YOGENDRA YOGI, SCHUGARDT JOHN, AUKLAND DANIEL, MANSOUR MAHMOUD, FROST CRISTOPHER, GREENMAN MATT, Nasir, Shakeel, Sheoran, Yogendra Yogi, Schugardt, John, Aukland, Daniel, Mansour, Mahmoud, Frost, Cristopher, Greenman, Matt
Принадлежит: HONEYWELL INTERNATIONAL INC.

A method for scavenging small particles from a turbine engine includes directing compressed air through a flowpath, downstream of a compressor, which causes a reduction in a radial flow component and the introduction of or an increase in an axial flow component of the compressed air, removing a portion of the compressed air from the flowpath and directing the portion into a scavenge plenum, the scavenge plenum being positioned adjacent to and radially outward from the flow path, and returning the portion of the compressed air from the plenum to the flowpath while maintaining a majority of the small particles that were present in the portion within the scavenge plenum. Further, the method includes removing the majority of small particles from the plenum. The step of removing occurs intermittently during engine operation, during engine shutdown, or while the engine is not operation, but does not occur continuously during engine operation.

Подробнее
Номер записи: 3