Airfoil core shape for a turbomachine component

A turbomachine component includes a compressor stator vane having an airfoil core shape. The airfoil core shape includes a nominal profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in TABLE 1, and wherein X and Y are distances in inches which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z in inches. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil core shape.

Rotor and guide blades designing method for turbo-machine i.e. gas turbine engine, involves running skeleton curve in profile section in sectional line angle distribution area lying between upper and lower limit curves

The method involves defining a skeleton curve by a skeleton line angle over a chord length, leading edge (2), blade height (h) and a blade spike (6). The curve is run in a blade profile section, which is present in an area running out of the blade spike up to 30 percentages of the blade height, in a sectional line angle distribution area lying between upper and lower limit curves. A pressure load is produced along a blade surface in the distribution area. Dimensionless skeleton line angles at a position of the chord length are provided for the limit curves from a specific formula.

Blade of a fluid flow machine with block-defined profile skeleton line

Die Erfindung bezieht sich auf eine Strömungsarbeitsmaschinenschaufel mit einer Profilskelettlinie, welche sich längs einer Meridianstromlinie erstreckt, wobei die Schaufel in radialer Richtung in mindestens drei Zonen (Z0, Z1, Z2) unterteilt ist und wobei die jeweils radial innere und die radial äußere Profilskelettlinie jeder Zone (Z0, Z1, Z2) so ausgebildet ist, dass die folgenden Gleichungen genügen: DOLLAR F1 wobei DOLLAR A - P ein beliebiger Punkt der Profilskelettlinie, DOLLAR A - alpha¶1¶ der Neigungswinkel an der Schaufel-Vorderkante, DOLLAR A - alpha¶2¶ der Neigungswinkel an der Schaufel-Hinterkante, DOLLAR A - alpha* der dimensionslose, bezogene Winkel der Gasamtwölbung, DOLLAR A - S* die dimensionslose, bezogene Lauflänge, DOLLAR A - alpha¶P¶ der Winkel der Tangente an einem beliebigen Punkt P der Profilskelettlinie zur mittleren Meridianstromlinie, DOLLAR A - S¶P¶ die Lauflänge der Profilskelettlinie an einem beliebigen Punkt P, und DOLLAR A - S die Gesamtlauflänge der Profilskelettlinie sind. The invention relates to a fluid flow machine blade with a profile skeleton line which extends along a meridian streamline, the blade being divided in the radial direction into at least three zones (Z0, Z1, Z2) and with the radially inner and the radially outer profile skeleton line of each zone (Z0, Z1, Z2) is designed such that the following equations are sufficient: DOLLAR F1 where DOLLAR A - P is any point on the profile skeleton line, DOLLAR A - alpha¶1¶ the angle of inclination at the front edge of the blade, DOLLAR A - alpha¶ 2¶ the angle of inclination at the trailing edge of the blade, DOLLAR A - alpha * the dimensionless, related angle of the gas curvature, DOLLAR A - S * the dimensionless, related barrel length, DOLLAR A - alpha¶P¶ the angle of the tangent at any point P the profile skeleton line to the middle meridian current line, DOLLAR A - S¶P¶ the length of the profile skeleton line at any point P, and DOLLAR A - S the total length length of the ...

Impeller for a gas turbine

Blade of an axial flow machine

Es wird eine Schaufel einer Axialströmungsmaschine vorgeschlagen, umfassend: eine zur Erzeugung eines Überdrucks zwischen einer Vorderkante (11) und einer Hinterkante (12) ausgebildete Hohlseite (13) und eine zur Erzeugung eines Unterdrucks zwischen der Vorderkante (11) und der Hinterkante (12) ausgebildete Rückseite (14). Eine Skelettlinie (CLo) in der Hinterkante (12) umfasst einen ersten gekrümmten Abschnitt (Q1), der zu der Hohlseite (13) hin gekrümmt ist, sowie einen zweiten gekrümmten Abschnitt (Q2), der hinter dem ersten gekrümmten Abschnitt (Q1) angeordnet ist und zur Rückseite (14) hin gekrümmt ist, wobei der zweite gekrümmte Abschnitt (Q2) eine sich von der Seite einer Schaufelwurzel zu einer Schaufelspitze hin verringernde Krümmung aufweist. A blade of an axial flow machine is proposed, comprising: a hollow side (13) designed to generate an overpressure between a front edge (11) and a trailing edge (12) and one for generating a negative pressure between the front edge (11) and the trailing edge (12) trained back (14). A skeleton line (CLo) in the trailing edge (12) includes a first curved portion (Q1) curved toward the hollow side (13) and a second curved portion (Q2) disposed behind the first curved portion (Q1) and curved toward the rear side (14), the second curved portion (Q2) having a curvature decreasing from the side of a blade root toward a blade tip.

Rotor, device converting energy of liquid medium flow, device forming fluid medium flow (versions) and pump

FIELD: pumps and turbines. SUBSTANCE: rotor used in device forming fluid medium flow or converting energy of fluid medium flow is mounted for rotation relative to central axis and is provided with working surface whose directrix sets bow-shaped line of motion of fluid medium flow located around central axis of rotation of rotor. This directrix of working surface has form of logarithmic curve which corresponds to mathematical progression known as golden section or Fibonaci progression. EFFECT: reduction of wear; enhanced efficiency. 33 cl, 17 dwg 95908 91сС ПЫ с» (19) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ ВИ `” 2 168 066 (51) МПК” (13) С2 Е 040 1/04, 17/06, 29/18, 29/28, 29/66, Е 03 В 3/00, Е 01 0 1/34 (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 98102415/06, 08.07.1996 (24) Дата начала действия патента: 08.07.1996 (30) Приоритет: 10.07.1995 АЧ РМ 4072 05.09.1995 АЧ РМ 5249 11.03.1996 АЧ РМ 8580 (43) Дата публикации заявки: 20.12.1999 (46) Дата публикации: 27.05.2001 (56) Ссылки: 4$ 3082695 А, 26.03.1963. 4$ 4540334 А, 10.09.1985. КУ 2013662 СЛ, 30.05.1994. 9$ 2165808 А, 11.09.1939. КУ 2130 (1, 05.05.1996. 5Ц 4793398 А, 19.01.1983. 0$ 4708585 А, 24.11.1987. (85) Дата перевода заявки РСТ на национальную фазу: 10.02.1998 (86) Заявка РСТ: АЦ 96/00427 (08.07.1996) (87) Публикация РСТ: М/О 97/03291 (30.01.1997) (98) Адрес для переписки: 103055, Москва, а/я 11, Попеленскому Н.К. (71) Заявитель: ХАРМЭН Джейден Дэвид (АЦ) (72) Изобретатель: ХАРМЭН Джейден Дэвид (АЦ) (73) Патентообладатель: ХАРМЭН Джейден Дэвид (АЦ) (74) Патентный поверенный: Попеленский Николай Константинович (54) РОТОР, УСТРОЙСТВО, ПРЕОБРАЗУЮЩЕЕ ЭНЕРГИЮ ПОТОКА ТЕКУЧЕЙ СРЕДЫ, УСТРОЙСТВО, СОЗДАЮЩЕЕ ПОТОК ТЕКУЧЕИ СРЕДЫ (ВАРИАНТЫ) И НАСОС (57) Изобретения могут быть использованы в насосах и турбинах. Ротор для использования в устройстве, создающем поток текучей среды или преобразующем энергию потока текучей среды, установлен с возможностью вращения относительно ...

轴向流动送风机

本发明通过改进用于例如空调的室外装置的送风机的叶片结构而提供一种能够减小噪音并且提高效率的送风机。其提供有叶轮（1），在该叶轮（1）中布置在周向上间隔地连接到轮毂（2）周表面上的多个叶片（3），并且叶片（3）的后缘具有凸形部分（30），其中其在径向上的中间部分弯曲以便扩展到吸入侧。凸形部分在叶片的叶片弦方向上从叶片的前缘和后缘之间开始，到达叶片的后缘，凸形部分的顶点位于叶片的后缘。通过采用这种结构，空气的排放速率沿着叶片（3）的径向能够变得均匀，并且变得能够减小噪音和提高效率。

Blade with asymmetrical platform, rotor blade wheel, turbomachine and turbomachine nozzle diaphragm section

FIELD: machine building. SUBSTANCE: blade (10) for turbomachine rotor blade wheel comprises an aerofoil section and at least one platform on the end of the aerofoil. The blade (10) is made so that to be set together with many other essentially similar blades so as to form a ring. The platform surface is fitted by profile (80) on the suction surface side and by profile (85) on the pressure surface side, respectively along the suction surface or pressure surface. The suction surface profile (85) of the blade has a recessed section (I) of the pressure surface located in the axial direction in the upstream half of the aerofoil section. Most of the surface between the aerofoil profiles is provided by the movement of a linear segment based on the profiles (80, 85) of suction surface and pressure surface. EFFECT: increased efficicency of blade and turbomachine due to reducing turbulence near the blade platform surface. 17 cl, 8 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 498 081 (13) C2 (51) МПК F01D 5/14 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2010139779/06, 27.02.2009 (24) Дата начала отсчета срока действия патента: 27.02.2009 (73) Патентообладатель(и): СНЕКМА (FR) (43) Дата публикации заявки: 10.04.2012 Бюл. № 10 2 4 9 8 0 8 1 (45) Опубликовано: 10.11.2013 Бюл. № 31 (56) Список документов, цитированных в отчете о поиске: US 2007/0258818 A1, 08.11.2007. US 4677828 A, 07.07.1987. JP 6-33703 A, 08.02.1994. US 6283713 B1, 04.09.2001. EP 1239116 A2, 11.09.2002. RU 2232922 C2, 20.07.2004. 2 4 9 8 0 8 1 R U (86) Заявка PCT: FR 2009/050318 (27.02.2009) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 28.09.2010 (87) Публикация заявки РСТ: WO 2009/112775 (17.09.2009) Адрес для переписки: 129090, Москва, ул.Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", пат.пов. А.В.Мицу, рег.№ 364 (54) ЛОПАСТЬ С НЕСИММЕТРИЧНОЙ ПОЛКОЙ, РАБОЧЕЕ ЛОПАСТНОЕ КОЛЕСО, ТУРБОМАШИНА И ...

Axial-flow fan

FIELD: mechanical engineering. SUBSTANCE: axial-flow fan 1 has central hub 3 and blades 4; each blade has root 5 and tip 6 and is bounded by convex edge 7 whose projection on plane of rotation of fan is defined by parabolic segment and concave edge 8 whose projection on plane of rotation of fan is defined by arc of circle. Blade 4 has sections with aerodynamic profiles 18 and surface 18a including at least one rectilinear section (t) and blade angle (β) which gradually and continuously reduces from blade root 5 to tip 6 of blade 4 according to cube root law as function of fan radius. EFFECT: higher efficiency. 11 cl, 8 dwg, 1 tbl РЗ 0Ссс ПЧ сэ (19) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ ВИ” 2 208 711‘ (51) МПК? 13) С2 Е 040 19/00, 29/38, 29/66 12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 2000126486/06, 18.03.1999 (24) Дата начала действия патента: 18.03.1999 (30) Приоритет: 23.03.1998 ЕР 98830169.3 (43) Дата публикации заявки: 10.12.2002 (46) Дата публикации: 20.07.2003 (56) Ссылки: 4$ 456932 А, 11.02.1986. КЦ 2011890 СЛ, 30.04.1994. 5Ц 1370320 А\, 30.01.1988. СВ 1335757 А, 31.10.1973. 4$ 4253800 А, 03.03.1981. (85) Дата перевода заявки РСТ на национальную фазу: 23.10.2000 (86) Заявка РСТ: 1В 9900459 (18.03.1999) (87) Публикация РСТ: М/О 99/49224 (30.09.1999) (98) Адрес для переписки: 129010, Москва, ул. Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", патентному поверенному Е.В.Томской, рег.№ 0106 (71) Заявитель: СПАЛ С.Р.Л. (11) (72) Изобретатель: СПАДЖАРИ Алессандро (1Т) (73) Патентообладатель: СПАЛ С.Р.Л. (1Т) (74) Патентный поверенный: Томская Елена Владимировна (54) ОСЕВОЙ ВЕНТИЛЯТОР (57) Осевой вентилятор (1) содержит центральную ступицу (3), большое количество лопаток (4) при этом каждая лопатка (4) имеет корневую часть (5) и концевую часть (6), а также ограничена выпуклой кромкой (7), проекция которой на плоскость вращения вентилятора определяется параболическим сегментом и вогнутой кромкой (8 ...

Apparatus and method for generating power from moving water

一种由水体中的水流产生动力的装置，包括：纵向延伸的漂浮平台，用于维持所述装置使其漂浮在水体中；和水轮机，其被平台可运转地承载，以响应于水体中的水流产生动力。所述平台被构造用于加强经过水轮机叶片的水流的流动，并且使各自具有相关水轮机或多个水轮机的许多相似平台以协作的方式排列。所述水轮机可包括水轮机转子，所述水轮机转子带有多个较窄的、柔性的细长叶片，所述叶片布置在沿着转子延伸的在圆周方向间隔开的各排中。在每一排中，叶片彼此连续地间隔开一个间距。各排可以互相交错排列，以便在给定的一排中的叶片沿着圆周方向与该给定排的沿圆周方向的紧向前方的排中的叶片之间的间距以及与该给定排的沿圆周方向的紧向后方的排中的叶片之间的间距对齐。

Wind turbine airfoil family

Mehrere Flügelprofile (140; 150, 160, 170, 180) für eine Windturbinenschaufel (100), wobei die Windturbine eine Windturbinennabe aufweist, wobei jedes Flügelprofil (140) aufweist:eine Vorderkante (200);eine stumpfe Hinterkante (210);eine Sehnenlinie (190), die sich von der Vorderkante (200) zu der stumpfen Hinterkante (210) erstreckt;eine im Wesentlichen ovale Saugseite (220) undeine im Wesentlichen S-förmige Druckseite (230),wobei die mehreren Flügelprofile (140; 150, 160, 170, 180) abnehmende Querschnittsflächen entlang der Windturbinenschaufel in einer von der Windturbinennabe weg verlaufenden Richtung aufweisen,wobei die im Wesentlichen ovalen Saugseiten (220) dimensionslose X/c- und positive Y/c-Koordinatenwerte aufweisen, wie sie in den Tabellen 1-4 angegeben sind, wobei die X/c-Werte Orte auf der Sehnenlinie (190) im Verhältnis zu der Hinterkante (210) darstellen und die Y/c-Werte Höhen von der Sehnenlinie (190) zu Punkten auf den Saugseiten (220) darstellen, oderwobei die im Wesentlichen S-förmigen Druckseiten (230) dimensionslose X/c- und negative Y/c-Koordinatenwerte aufweisen, wie sie in den Tabellen 1-4 angegeben sind, wobei die X/c-Werte Orte auf der Sehnenlinie (190) im Verhältnis zu der Hinterkante (210) darstellen und die negativen Y/c-Werte Höhen von der Sehnenlinie (190) zu Punkten auf den Druckseiten (230) darstellen. A plurality of airfoils (140; 150, 160, 170, 180) for a wind turbine blade (100), the wind turbine having a wind turbine hub, each airfoil (140) having: a leading edge (200); a blunt trailing edge (210); a chord line (190) extending from the leading edge (200) to the blunt trailing edge (210); a substantially oval suction side (220) and a substantially S-shaped pressure side (230), the plurality of airfoils (140; 150, 160 , 170, 180) have decreasing cross-sectional areas along the wind turbine blade in a direction away from the wind turbine hub, the essentially oval suction sides (220) having dimensionless X / c and positive Y / c ...

Wind turbine airfoil family

Es ist eine Familie von Flügelprofilen (140) für eine Windturbinenschaufel (100) beschrieben. Jedes Flügelprofil (140) kann eine stumpfe Hinterkante (210), eine im Wesentlichen ovale Saugseite (220) und eine im Wesentlichen S-förmige Druckseite (230) enthalten. A family of airfoils (140) for a wind turbine blade (100) is described. Each wing profile (140) may include a blunt trailing edge (210), a substantially oval suction side (220), and a substantially S-shaped pressure side (230).

Airfoil profile for an axial flow compressor that can reduce losses in the range of low Reynolds numbers

Flügelprofil für einen Axialströmungskompressor, das den Verlust in einem Bereich niedriger Reynolds-Zahlen senken kann, umfassend: eine innere Bogenfläche (13), welche derart ausgelegt ist, dass sie zwischen einer führenden Kante (11) und einer nachlaufenden Kante (12) einen positiven Überdruck erzeugt, und einen Bogenrücken (14), welcher derart ausgelegt ist, dass er zwischen der führenden und der nachlaufenden Kante (11 und 12) einen Unterdruck erzeugt, dadurch gekennzeichnet, dass eine Verteilung der Strömungsgeschwindigkeit an der Seite des Bogenrückens (14) einen einzelnen Überschall-Maximalwert innerhalb eines Bereichs von 6% bis 15% an einer Sehne von der führenden Kante (11) aus aufweist, wobei eine Position der führenden Kante (11) durch 0% repräsentiert ist und eine Position der nachlaufenden Kante (12) durch 100% repräsentiert ist. An airfoil blade profile for an axial flow compressor that can reduce the loss in a range of low Reynolds numbers, comprising: an inner arc surface (13) configured to be positive between a leading edge (11) and a trailing edge (12) Overpressure generated, and a sheet back (14) which is designed such that it generates a negative pressure between the leading and the trailing edge (11 and 12), characterized in that a distribution of the flow velocity at the side of the sheet back (14) supersonic maximum value within a range of 6% to 15% at a chord from the leading edge (11), wherein a position of the leading edge (11) is represented by 0% and a position of the trailing edge (12) 100% is represented.

Axial compressor cascade blade design curves outside and inside of blades to give under- and overpressure respectively and specified compensatory supersonic constant speed region for performance boost.

The curvature (Sp) of the inside of the blade (W) sets up an underpressure as against the curvature (Ss) of the outside of the blade which produces overpressure. The flow speed distribution on the outside curvature (Ss) behind a first high value and from the leading edge (E1) of the blade (W) over 15% of the length of the chord has a supersonic region basically constant flow speed. This region is such that the difference between the Mach numbers at front and rear edge of the supersonic region when divided by the supersonic length value in relation to the chord length is less than 1, the Mach number of the supersonic region to amount to less than 1.4.

Axial flow blower

본 발명은 축류송풍기에 관한 것으로서, 허브(12) 둘레에 복수의 날개(13)를 설치하고, 각 날개의 부압면 앞가장자리부(13b)에 그 앞가장자리 필렛부터 날개 뒷가장자리(13d)를 향하여 매끄럽게 연결되는 유선형 리브(14)를 복수개 설치하며, 각 유선형 리브는 그 중심축이 날개 바깥 둘레 앞가장자리측 원호부(13e)의 중심을 P로 한 경우, 이 P를 중심점으로 한 원호(α n )와 날개의 교점(S n )을 통과함과 동시에, 이 원호(α n )의 접선에 평행이 되도록 배치되어 있는 것으로, 날개의 부압면에서 발생하는 흐름의 박리에 의한 송풍음의 증가를 억제하고 성형성이 양호하고 가격이 저렴한 축류송풍기를 제공하는 것을 특징으로 한다. The present invention relates to an axial blower, wherein a plurality of wings (13) are provided around the hub (12), and the front edge fillet (13b) of the negative pressure surface of each wing is directed from the front fillet (13d) to the wing rear edge (13d). A plurality of streamlined ribs 14 connected smoothly are provided, and each streamlined rib has an arc (α n ) centered on this P when its center axis is the center of the circular arc portion 13e on the outer edge of the wing. It is arranged to be parallel to the tangent of the circular arc (α n ) while passing through the intersection point (S n ) of the blade) and the blade, and suppresses the increase of the blowing sound due to the separation of the flow generated at the negative pressure surface of the blade. And it is characterized by providing an axial blower with good moldability and low cost.

Impeller

A pump impeller for a centrifugal pump The impeller is defined by a shroud rotatable about an axis of rotation At least two pump vanes extend axially from the shroud, each of the vanes configured as a blunted tear drop shape and having an inside wall and an outside wall, the leading edges of which are interconnected by a blunt wall The trailing edges of the inside and outside walls merge together A substantially constant width flow channel is defined between the blunted wall of one vane and a confronting surface defined by an inside wall of the other vane The vanes are tapered in the axial directions by inclining the inside wall of each vane radially outwardly.

Wind turbine airfoil family

用于风力涡轮机叶片(100)的翼型(140)族。每个翼型(140)可以包括钝的后缘(210)、大致卵形的吸力侧(220)和大致S形的压力侧(230)。

Compressor rotating blade for axial compressor

Изобретение относится к компрессорной рабочей лопатке (10) для компрессоров с осевым потоком предпочтительно стационарных газовых турбин. Предусмотрено, что для уменьшения потерь в радиальном зазоре средняя линия (32) расположенных на стороне вершины лопатки профилей (30) пера (12) компрессорной рабочей лопатки (10) имеет по меньшей мере две точки (36, 38) перегиба. За счет наличия двух точек (36, 38) перегиба получаются для контура (42) стороны всасывания на участке от 35% до 50% длины хорды профиля участок (D) контура стороны всасывания, который выполнен вогнутым, и для контура (40) стороны давления участок (Е) контура стороны давления, который выполнен выпуклым. С помощью этой геометрии обеспечивается возможность генерирования приводящего к меньшим потерям вихря в зазоре с целью повышения общего коэффициента полезного действия снабженного этими компрессорными рабочими лопатками (10) осевого компрессора. 2 н. и 15 з. п. ф-лы, 10 ил., 1 табл. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F04D 29/32 (13) 2 534 190 C2 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2012112930/06, 10.08.2010 (24) Дата начала отсчета срока действия патента: 10.08.2010 Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): КРЕГЕР Георг (DE), КОРНЕЛИУС Кристиан (DE), НИККЕ Эберхард (DE) 04.09.2009 EP 09011392.9 (43) Дата публикации заявки: 10.10.2013 Бюл. № 28 R U (73) Патентообладатель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (45) Опубликовано: 27.11.2014 Бюл. № 33 1998059175 A1, 30.12.1998. SU 521401 A1, 15.07.1976. RU 2220329 C2, 27.12.2003 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 04.04.2012 (86) Заявка PCT: 2 5 3 4 1 9 0 (56) Список документов, цитированных в отчете о поиске: DE 102005025213 A1, 07.12.2006. WO 2 5 3 4 1 9 0 R U (87) Публикация заявки PCT: WO 2011/026714 (10.03.2011) Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры" (54 ...

Wind sail receptor

本发明涉及一种在风或水流中旋转的风帆接收器，其使轴旋转，该轴则使发电装置工作而产生电能输出，用于做功或者将电能输出传输到储存设备。优选的是，所述风帆接收器包括位于后轮毂和前盘之间的六到十片等距间隔开的相同叶片，后轮毂和前盘都与轴相连，该轴经由轴承安装到框架上，从而使得风帆接收器在面向风或水流时可以自由旋转。所述风帆接收器叶片由两组三至五片等距间隔开的叶片构成，每组由单片刚性材料的平展部分构成，从所述单片平展部分去除若干径向部分而形成围绕轮毂等距间隔开的各个叶片，将轮毂安装到彼此上，将叶片弯折成同样的曲形，并且叶片外端以相等的间距固定到前盘上，从而形成所述风帆接收器。

Skewed axial fan assembly

프리-팁형 축류 팬 조립체는 팬 노이즈를 저감하면서 반경방향 팁 편향을 최소화하는 비대칭 분포를 갖는다. 팬 반경에서 전연 에지 비대칭 값과 전연 에지 비대칭 최대값 간의 차이는 적어도 10°이다. 팬 반경에서 후연 에지 비대칭 값과 후연 에지 비대칭 최대값 간의 차이에 대한 팬 반경에서 전연 에지 비대칭 값과 전연 에지 비대칭 최대값 간의 차이의 비율은 적어도 2.5이다.

A single or multi-bladed rotor

회전자가 회전축에 연결되어 고정되는 허브(12)와 상기 허브(12)에 그 일측단부가 연결되는 적어도 하나 이상의 방사형의 블레이드를 포함하고, 상기 적어도 하나의 블레이드는 등각의 반경에서 측정된 곡선의 반경의 성장의 차수가 일정하며, 5 : 8의 비율에 일치하는 황금분할과 실질적으로 일치하는 로그함수적 곡선의 배치를 갖는 유체반응면(14)을 갖는, 단일 또는 다수의 블레이드를 갖는 회전자를 제공한다. A hub 12 having a rotor connected to and fixed to the axis of rotation and at least one radial blade having one end connected to the hub 12, the at least one blade having a radius of a curve measured at an equiangular radius; Rotors with single or multiple blades, with fluid response surface 14 having a constant order of growth and having a logarithmic curve arrangement substantially coincident with the golden division corresponding to a ratio of 5: 8 to provide. 회전자, 황금분할, 블레이드, 유체반응면, 만곡부, 로그함수적 곡선 Rotor, Golden Split, Blade, Fluid Reaction Surface, Curved Section, Logarithmic Curve

Blade profile for wind turbine

Tail rotor of a helicopter

A tail rotor of a helicopter comprising a hub with at least two blades hinged to it, each blade having a sweep angle selected in combination with transverse displacement, and a rod controlling the collective pitch of the rotor, said rod carrying an articulated blade-pitch control means.

Blade-shaped portion for turbine nozzle

【課題】タービンノズル用の翼形部形状を提供する。 【手段】本製品（２３０）は、表Ｉに記載のＸ、Ｙ及びＺのデカルト座標値に実質的に合致する基準輪郭を有する。Ｘ及びＹ値は、滑らかな連続円弧で結ぶと、インチ単位で表す各距離Ｚにおける翼形部輪郭断面（２５０）を定めるインチ単位で表す距離である。Ｘ、Ｙ及びＺ距離は、拡大又は縮小したノズル用の翼形部断面を得るために同一の定数又は数値の関数として拡大縮小可能である。Ｘ、Ｙ及びＺ距離で与えられた基準翼形部は、＋０．１３０インチ〜−０．０３０インチの包絡面内に位置する。 【選択図】 図２

Rotor blade for high-speed gyrodyne aircraft

Изобретение относится к области авиации, более конкретно к лопасти несущего винта винтокрылого летательного аппарата. Лопасть несущего винта выполнена таким образом, что хорда лопасти увеличивается от корневой области лопасти к основной области лопасти и уменьшается от основной области к области законцовки лопасти несущего винта. При этом лопасть может быть выполнена в таком варианте, в котором хорда лопасти увеличивается в пределах основной области лопасти до максимальной хорды лопасти несущего винта, содержащейся в основной области лопасти несущего винта, а затем уменьшается в пределах основной области лопасти снаружи от максимальной хорды лопасти несущего винта. Также возможно выполнение лопасти таким образом, что максимальная хорда лопасти несущего винта будет находиться между 65% R и 75% R пролета лопасти несущего винта, определяемого от оси вращения лопасти до дистального конца области законцовки лопасти для определения эллиптического распределения. Технический результат заключается в создании лопасти несущего винта винтокрылого летательного аппарата для режима поступательного полета на скоростях свыше 250 узлов. 3 н. и 27 з.п. ф-лы, 12 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 408 499 (13) C2 (51) МПК B64C 27/32 B64C 27/46 (2006.01) (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2007148890/11, 28.04.2006 (24) Дата начала отсчета срока действия патента: 28.04.2006 (73) Патентообладатель(и): СИКОРСКИ ЭРКРАФТ КОРПОРЕЙШН (US) (43) Дата публикации заявки: 10.07.2009 Бюл. № 19 R U (45) Опубликовано: 10.01.2011 Бюл. № 1 2 4 0 8 4 9 9 Приоритет(ы): (30) Конвенционный приоритет: 31.05.2005 US 11/140,706 (72) Автор(ы): БАГАИ Ашиш (US), МОФФИТТ Роберт С. (US), БЛЭКУЭЛЛ Роберт Х. (US), КРАУСС Тимоти А. (US) (56) Список документов, цитированных в отчете о поиске: US 6000911 А, 14.12.1999. US 4248572 А, 03.02.1981. RU 2204503 C2, 20.05.2003. US 5782607 A, 21.07.1998. 2 4 0 8 4 9 ...

Sailing Windmill

1. Парусный ветряк, включающий первую и вторую секции лопастей, каждая из которых имеет от трех до пяти радиально расположенных одинаковых лопастных частей, при этом секции лопастного устройства расположены друг за другом и соединены в их центрах, формируя заднюю центральную ступицу, причем каждая из лопастей образована с заданным изгибом в ее центральной секции, который определяется отношением осевого расстояния между задней ступицей и передним диском, которое составляет от 0,75 до 0,85 длины лопасти от точки ее соединения с задней ступицей до конца лопасти, который прикреплен к переднему диску; при этом концы каждой лопасти напротив их соединения с задней ступицей закреплены на равном радиальном расстоянии в равно расположенных точках вокруг переднего диска; при этом вал закрепляет на себе секцию задней ступицы и передний диск парусного ветряка, и выходит из любой или сразу из обоих секций задней ступицы и переднего диска; и предусмотрена опора для крепления вала, обеспечивая его свободное вращение. ! 2. Парусный ветряк по п.1, в котором одинаковые лопасти каждой секции парусного ветряка имеют по существу прямую переднюю кромку, включают закругленную секцию задней кромки, прилегающую к внутреннему краю, прикрепленному к секции задней ступицы и на наружной стороне секцией прямой кромки, которая проходит к концу лопасти. ! 3. Парусный ветряк по п.2, в котором одинаковые концы лопастей ограничиваются передней и задней кромками. ! 4. Парусный ветряк по п.1, в котором каждый внутренний конец передней кромки лопастей закрепляется в расположенных на равных расстояниях радиальных отверстиях, которые сформированы в перед� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2008 122 990 (13) A (51) МПК F04D 29/26 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21), (22) Заявка: 2008122990/06, 23.10.2006 (71) Заявитель(и): СТЕЙНКЕ Ричард А. (US), МАКГУАЙР Джон К. (US) (30) Конвенционный приоритет: 07.11.2005 US 11/270,403 ...

Manufacture of blade form for rotor blade

(57)【要約】本公報は電子出願前の出願データであるた め要約のデータは記録されません。

High efficiency stator for the first phase of a gas turbine

본 발명은 데카르트 좌표계(X, Y, Z)에서, 각각 개별 조합 점의 좌표에 의해 한정된 일련의 블레이드(1)를 갖는 저압 터빈의 제 1 단용 고정자이며, 축(Z)은 터빈의 중심축과 교차하는 반경방향 축인 고정자를 개시한다. The present invention is a stator for a first stage of a low pressure turbine having a series of blades (1) defined in the Cartesian coordinate system (X, Y, Z), each defined by the coordinates of the respective combination points, the axis Z being the central axis of the turbine and Initiate a stator that is an alternating radial axis. 각 블레이드(1)의 프로파일은 중심축으로부터 거리(Z)에 놓여진 평면(X, Y)과 프로파일 자체 사이의 일련의 교차 폐곡선(20)에 의해 이루어진다. The profile of each blade 1 is made up of a series of intersecting closed curves 20 between the plane X, Y lying at a distance Z from the central axis and the profile itself. 각 블레이드(1)는 블레이드의 중간 높이에서의 평균 스로트 길이와 평균 스로트 지점의 반경에서 구해진 원주방향 피치 사이의 비율의 코사인 아크에 의해 규정된 평균 스로트 각도를 가지며, 평균 스로트 각도의 범위는 57°내지 60°이다. Each blade 1 has an average throat angle defined by a cosine arc of the ratio between the average throat length at the middle height of the blade and the circumferential pitch found at the radius of the average throat point, The range is 57 ° to 60 °.

Non-axisymmetric end wall contouring for a turbomachine blade row

A turbomachine blade row is provided having a hub that includes a non-axisymmetric end wall modified by a transformation function. The blade row further includes a circumferential row of a plurality of airfoil members radially extending from the non-axisymmetric end wall of the hub and forming a plurality of sectoral passages therebetween. A radius of the non-axisymmetric end wall is determined by a transformation function including a plurality of geometric parameters defined by a user based on flow conditions. The plurality of geometric parameters provide for modification of the end wall in both an axial and a tangential direction to include a plurality of concave profiled regions and convex profiled regions.

Axial turbine

本发明的目的在于提供一种轴流式涡轮机，它可以抑制流入动叶的流体相对于动叶的相对速度并提高涡轮机的级效率。本发明的轴流式涡轮机，具有多级由定叶(41)和与该定叶(41)的工作流体流动方向的下游侧相对的动叶(42)构成的涡轮机级，其特征是，将定叶(41)做成：构成具有叶片长度比前级的动叶长的动叶(42)的级的定叶(41)的外周部和包含涡轮机中心轴(21)的面相交的定叶外径线(4)线至少含有该定叶(41)的出口外周部(3)并具有与涡轮机中心轴(21)平行的流道直径相同部分(60)。

Improve impact resistance of hollow airfoil

Non-fouling kinetic hydro power system axial-flow blade tip treatment

This relates to a modified turbine blade tip design using a fairing shaped design that increases the tip area efficiency of a kinetic hydropower turbine rotor blade while having a non-fouling characteristic and a tip design with the ability to shed weeds, debris, or other submerged materials that might have fouling potential.

Kinetic hydro energy conversion system

A kinetic hydro energy conversion system having a turbine for mounting in a hydro energy source, wherein the turbine comprises a rotor having conformal blades and a screen for horizontally deflecting debris from the blades.

Turbo fan of Window type Air conditioner

본 발명은 창문형 에어컨에 적용되는 터보팬에 관한 것으로, 본 발명의 실시예에 따른 터보팬은 허브(204)와, 상기 허브(204)에 일정간격을 두고 배치되며, 허브(204) 측에서 슈라우드(203) 측으로 갈수록 그 폭이 줄어드는 형태로 구성되는 7 ~ 11개의 블레이드(205)와, 상기 허브(204)의 반대측에서 각 블레이드(205)에 공통 연결된 슈라우드(203)를 포함하여 구성되며; 전체폭(W)이 블레이드 외경(D 2 )의 35 ~ 45%, 출구폭(W 2 )이 상기 전체폭(W)의 50 ~ 60%, 입구폭(W 1 )이 상기 전체폭(W)의 85 ~ 92%, 블레이드(205)의 허브 측 내경(Dh 1 )이 블레이드 외경(D 2 )의 45 ~ 55%, 블레이드(205)의 슈라우드 측 내경(Ds 1 )이 블레이드 외경(D 2 )의 60 ~ 70% 로 이루어진다. The present invention relates to a turbofan applied to a window air conditioner, the turbofan according to an embodiment of the present invention is disposed at a predetermined interval on the hub 204, the hub 204, the shroud at the hub 204 side 7 to 11 blades 205 configured to have a width decreasing toward the 203 side, and a shroud 203 commonly connected to the respective blades 205 on the opposite side of the hub 204; Full width (W) is 35 to 45% of blade outer diameter (D 2 ), outlet width (W 2 ) is 50 to 60% of the full width (W), inlet width (W 1 ) is the full width (W) 85 to 92% of blade 205, hub side inner diameter (Dh 1 ) is 45 to 55% of blade outer diameter (D 2 ), shroud side inner diameter (Ds 1 ) of blade 205 is blade outer diameter (D 2 ) Of 60 to 70% of the total. 여기서, 상기 각 블레이드(205)는 30 ~ 60˚의 슈라우드 측 경사각( )과, 55 ~ 65°의 출구각( 2 )과, 15 ~ 30°의 허브 측 입구각( h 1 )과, 40 ~ 55°의 슈라우드 측 입구각( s 1 )과, 0.3 ~ 0.5 의 최대 캠버위치(P)와, 허브 측 현(Lh 1 ) 길이의 5 ~ 8% 내지는 슈라우드 측 현(Ls 1 ) 길이의 7 ~ 12% 인 최대두께(t)를 갖는 형태로 이루어진다. Here, each of the blades 205 has a shroud side inclination angle of 30 to 60 degrees ( ) And an exit angle of 55 to 65 ° ( 2 ) and the hub side inlet angle of 15 to 30 ° ( h 1 ) and the shroud side inlet angle of 40 to 55 ° ( s 1 ), the maximum camber position (P) of 0.3 to 0.5 and the maximum thickness (t) of 5 to 8% of the length of the hub side string (Lh 1 ) or 7 to 12% of the length of the shroud side string (Ls 1 ). It is made in the form having. 또한, 상기 슈라우드(203)의 내경(Ds)은 블레이드 외경(D 2 )의 70 ~ 80% 인것을 특징으로 한다. In addition, the inner ...

Window type air conditioner turbo fan

Modified wind turbine airfoil

The present invention relates in a broad aspect to a method for design and modification of airfoils useful for wind turbine applications, which airfoils possess smooth and stable characteristics in stall. These characteristics comprise: (1) No or very little tendency to double stall, (2) Insensitivity or little sensitivity of maximum lift to leading edge roughness, (3) High lift-drag ratio just before maximum lift, (4) Small variations of the aerodynamic loads in stall and (5) Sufficient aerodynamic damping to suppress blade vibrations in stall. The invention further relates to blades and/or airfoil sections in general which posses smooth and stabile characteristics in stall. Also, it relates to a method of implementing the desired shape on an airfoil or a wind turbine blade.

Air foil configuration for wind turbine

A balancing of aerodynamic optimization and structural optimization provides a wind turbine airfoil having substantially improved performance characteristics. Mathematic modeling yields maximum aerodynamic criteria that are coupled with a structural analysis to modify the optimum aerodynamic design into a balanced, substantially optimized airfoil configuration. The resulting airfoils have substantial performance impact on GAEP. The airfoil is based on the theoretical optimum aerodynamic structure modified as required to maximize structural integrity. The method for maximizing airfoil performance permits the design of airfoils of predictable performance while achieving necessary structural integrity. A family of airfoils having operational and structural characteristics with substantially enhanced performance capability includes thickness-to-chord ratios ranging from 14% to 45%.

In-line centrifugal fan

一在线离心混合流鼓风机(20)，包括一轴向延伸的进口管道(22)。一入口锥形体(28)设置在进口端(24)。一叶轮(30)设置在入口锥形体的下游并包括：一中心设置的背轮(32)，它由一电动机(44)而旋转；多个鼓风机叶片(34)，从背轮径向朝外延伸；以及一轮锥形体(36)，固定地连接于和外接于轮的叶片。一设置在叶轮下游的驱动腔(48)包括多个径向延伸的伸直翼(50)，它们将空气引导到出口端(26)。鼓风机构造成其声压级下降，效率提高。

Axial flow fan

본 발명에 따른 축류 팬(1)은 중심 허브(3)와, 뿌리부(5) 및 단부(6)를 각각 가지는 다수의 블레이드(4)를 구비하고, 그 블레이드는, 팬의 회전 평면에의 투영이 포물선 세그먼트에 의해 정의되는 볼록 엣지(7)와, 팬의 회전 평면에의 투영이 원호에 의해 정의되는 오목 엣지(8)에 의해 범위가 정해진다. 블레이드(4)는, 반경의 함수로서 변화의 3승 법칙에 따라 블레이드(4)의 뿌리부(5)로부터 단부(6) 쪽으로 서서히 그리고 일정하게 감소하는 블레이드 각(β)과 적어도 하나의 초기 선분(t)을 가지는 면(18a)을 가진 공기 역학적 프로파일(18)을 가진다. The axial fan 1 according to the present invention has a central hub 3 and a plurality of blades 4 each having a root portion 5 and an end portion 6, the blades of which are connected to the plane of rotation of the fan. The projection is defined by a convex edge 7 in which the parabolic segment is defined and a concave edge 8 in which the projection of the fan to the plane of rotation is defined by an arc. The blade 4 is a blade angle β and at least one initial line segment that slowly and consistently decreases from the root portion 5 of the blade 4 toward the end 6 according to the quadratic law of change as a function of radius. It has an aerodynamic profile 18 with facet 18a having (t). 축류 팬, 블레이드, 볼록 엣지, 오목 엣지, 포물선 세그먼트, 원호 Axial fans, blades, convex edges, concave edges, parabolic segments, arcs

Francis turbine for the generation of hydro-electricity has blade profile ratio minimizing trailing edge vortices

A Francis turbine has a rotating array of turbine blades rotating on a hub and enclosed within a rotating shroud. Each blade has a root, a tip, a leading edge and a trailing edge. The distance Rc between the axis of rotation (1) and the shroud (7), divided by the distance Rb between the axis of rotation (1) and the root end (14), is a ratio between 0.2 and 04.

Wind turbine blade

本发明提供了一种风轮机，该风轮机包括具有高升力和/或低实度的风轮机叶片。该叶片用于俯仰调整式风轮机，该风轮机在可变转子速度下运行，并具有长度大于约30米的叶片。叶片例如有利地在于可在相同或接近相同的电力生产量下减少极限载荷和疲劳载荷。

Turbine blade with aerodynamic profile (versions) and turbine

Лопатка турбины включает в себя аэродинамический профиль, основание, хвостовик и деталь для соединения типа «ласточкин хвост». Лопатка имеет номинальный профиль внутренней центральной части по существу в соответствии со значениями X, Y и Z прямоугольных координат, приведенными в таблице I. Значения Z представляют собой безразмерные значения от 0 до 1, преобразуемые в расстояния Z в дюймах путем умножения значений Z на высоту лопатки в дюймах. Значения X и Y представляют собой расстояния в дюймах, которыми после соединения плавными непрерывными дугами задаются сечения профиля внутренней центральной части на каждом расстоянии Z вдоль лопатки. Сечения профиля на расстояниях Z соединены плавно друг с другом для образования указанного профиля внутренней центральной части лопатки. Расстояния X, Y и Z могут быть пропорционально изменены в зависимости от одной и той же постоянной или числа для получения пропорционально увеличенного или пропорционально уменьшенного профиля внутренней центральной части. Номинальный профиль внутренней центральной части, задаваемый расстояниями X, Y и Z, укладывается на огибающей с точностью ±0,039 дюйма в направлениях, нормальных к любому месту поверхности внутреннего центрального участка. Изобретение позволяет улучшить аэродинамическую эффективность. 3 н. и 7 з.п. ф-лы, 8 ил., 1 табл. ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (11) 2 342 538 (13) C2 (51) ÌÏÊ F01D 5/14 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2004107263/06, 11.03.2004 (30) Êîíâåíöèîííûé ïðèîðèòåò: 12.03.2003 US 10/385,438 (73) Ïàòåíòîîáëàäàòåëü(è): ÄÆÅÍÅÐÀË ÝËÅÊÒÐÈÊ ÊÎÌÏÀÍÈ (US) (43) Äàòà ïóáëèêàöèè çà âêè: 27.09.2005 R U (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 11.03.2004 (72) Àâòîð(û): ÁÐÈÒÒÈÍÃÕÝÌ Ðîáåðò Àëàí (US), ÁÅÍÄÆÀÌÈÍ Ýäâàðä Äàðåëë (US), ÏÅÐÐÈ Äæåéêîá Ê. II (US) (45) Îïóáëèêîâàíî: 27.12.2008 Áþë. ¹ 36 2 3 4 2 5 3 8 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: ...

Gas turbine

The pressure ratio DELTA P4S of a final stage moving blade is reduced. As a result, the Mach number in the final stage moving blade can be suppressed, and in the gas turbine operating at a pressure ratio of 20 or more, therefore, decline of turbine efficiency due to shock wave loss can be prevented securely. <IMAGE>

Patent JPS5949437B2

Turbine cascade

Sailing windmill

FIELD: power industry. ^ SUBSTANCE: sailing windmill includes the first and the second sections of blades, each of which has three to five radially located similar blade parts. Sections of sailing windmill are located one after the other and connected at their centre so that rear hub is formed. Each of blades is formed with the specified bending which is determined with ratio of axial distance between rear hub and front disc, which is 0.75 to 0.85 of length of blade from its connection point to rear hub to the end of blade, which is attached to front disc; at that, ends of each blade opposite their connection to rear hub are fixed at equal radial distance at equally spaced points about front disc. Rear hub and front disc of sailing windmill are fixed on the shaft, and shaft comes out either from rear hub or from front disc or from both of them; at that, support for attachment of shaft is provided so that its free rotation is provided. ^ EFFECT: effective wind or water energy conversion at simple design and economy in the production. ^ 9 cl, 7 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 419 726 (13) C2 (51) МПК F03D 1/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2008122990/06, 23.10.2006 (24) Дата начала отсчета срока действия патента: 23.10.2006 (72) Автор(ы): СТЕЙНКЕ Ричард А. (US), МАКГУАЙР Джон К. (US) R U (73) Патентообладатель(и): СТЕЙНКЕ Ричард А. (US), МАКГУАЙР Джон К. (US) Приоритет(ы): (30) Конвенционный приоритет: 07.11.2005 US 11/270,403 (43) Дата публикации заявки: 20.12.2009 Бюл. № 35 2 4 1 9 7 2 6 (45) Опубликовано: 27.05.2011 Бюл. № 15 (56) Список документов, цитированных в отчете о поиске: US 2098107 А, 02.11.1937. US 5083963 А, 28.01.1992. RU 31614 U1, 20.08.2003. SU 1834416 А1, 20.11.1995. 2 4 1 9 7 2 6 R U (86) Заявка PCT: US 2006/041404 (23.10.2006) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 07.06.2008 (87) Публикация ...

Compressor blade (versions) and its application

FIELD: compressors for stationary gas turbines. SUBSTANCE: profile of proposed blade provides for especially low aerodynamic losses when blade is washed off at high Reynolds number. EFFECT: low aerodynamic losses. 11 cl, 6 dwg осегегс пы сэ (19) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (51) МПК? 13) ВИ "” 2191 930 ' Е 040 29/32 С2 12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 2000101807/06, 15.06.1998 (24) Дата начала действия патента: 15.06.1998 (30) Приоритет: 24.06.1997 ОЕ 19726847.1 (43) Дата публикации заявки: 20.12.2001 (46) Дата публикации: 27.10.2002 (56) Ссылки: ОЕ 3141948, 15.04.1982. ЗИ 907311 А, 28.02.1982. $Ц 619692 А, 04.08.1978. $4 958717А, 25.09.1982. СВ 2104975 А, 16.03.1983. СВ 1294407 А, 25.10.1972. ЕК 2323043 АЛ, 01.04.1977. (85) Дата перевода заявки РСТ на национальную фазу: 24.01.2000 (86) Заявка РСТ: ОЕ 98/01620 (15.06.1998) (87) Публикация РСТ: М/О 98/59175 (30.12.1998) (98) Адрес для переписки: 103735, Москва, ул. Ильинка 5/2, "СОЮЗПАТЕНТ", А.А. Силаевой (71) Заявитель: СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (0Е) (72) Изобретатель: КЕЛЛЕР Ульф (ОЕ), МЕНИГ Рейнхард (0Е) (73) Патентообладатель: СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (0Е) (74) Патентный поверенный: Силаева Алла Александровна (54) КОМПРЕССОРНАЯ ЛОПАТКА (ВАРИАНТЫ) И ЕЕ ПРИМЕНЕНИЕ (57) Изобретение относится к компрессорной лопатке, в частности, для компрессора стационарной газовой турбины. Профиль лопатки компрессорной лопатки выполнен так что при обтекании компрессорной лопатки с большим числом Рейнольдса и с ВЫСОКОЙ степенью турбулентности получаются особенно низкие аэродинамические потери. 4 с. и 7 з.п. Ф-лы, бил. 2191930 С2 КО осегегс пы сэ КУЗЗАМ АСЕМСУ ГОК РАТЕМТ$ АМО ТКАОЕМАКК$ (19) ВИ "” 2191 930 ' 13) С2 51’ р 040 29/32 12) АВЗТКАСТ ОЕ 1МУЕМТОМ (21), (22) АррИсаНоп: 2000101807/06, 15.06.1998 (24) ЕНесНуе дае Гог ргорейу па: 15.06.1998 (30) Рношу: 24.06.1997 ОЕ 19726847.1 (43) АррИсаноп рибИзпеа: 20.12.2001 (46) Рае от риубИсаНоп: 27.10.2002 (85) Соттепсетеп{ о{ ...

High efficiency last stage bucket for steam turbine

A turbine bucket including a bucket airfoil having an airfoil shape is provided. The airfoil shape has a nominal profile according to the tables set forth in the specification. The X and Y coordinate are smoothly joined by an arc of radius R defining airfoil profile sections at each distance Z. The profile sections at the Z distances are joined smoothly with one another to form a complete airfoil shape. The airfoil profile results in improved efficiency and airfoil loading capability.

Second-stage turbine bucket airfoil

The second-stage buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in inches in Table I wherein Z is a perpendicular distance from a plane normal to a radius of the turbine centerline and containing the X and Y values with the Z value commencing at zero in the X, Y plane at the radially innermost aerodynamic section of the airfoil and X and Y are coordinate values defining the airfoil profile at each distance Z. The X, Y and Z values may be scaled as a function of the same constant or number to provide a scaled-up or scaled-down airfoil section for the bucket.

Rotor blade (versions) and turbine unit

FIELD: machine building. SUBSTANCE: rotor blade having a platform, a body part, connected to the platform, and a surface finished at the end part and having an aerodynamic shape in the cross section. The thickness of the rotor blade varies depending on its height according to three different linear functions: T max =-0.8646*h+1.1087, T max =-1.0209*h+1.2058, T max =-0.7618*h+0.9985, where h is the percentage of the blade height. The blade thickness can be put in compliance with the operation characteristics of the turbine unit. EFFECT: characteristics optimisation. 10 cl, 1 tbl, 5 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 581 501 C2 (51) МПК F01D 5/14 (2006.01) F04D 29/32 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2011135181/06, 24.08.2011 (24) Дата начала отсчета срока действия патента: 24.08.2011 Приоритет(ы): (30) Конвенционный приоритет: (72) Автор(ы): ЛАНЕСЕ Никола (IT), ЛОРУССО Сальваторе (IT), АРИНЧИ Паоло (IT), ГРИМАЛЬДИ Антонио Мария (IT) (43) Дата публикации заявки: 27.02.2013 Бюл. № 6 R U (73) Патентообладатель(и): Нуово Пиньоне С.п.А. (IT) 25.08.2010 IT CO2010A000045 (45) Опубликовано: 20.04.2016 Бюл. № 11 2 5 8 1 5 0 1 R U (54) РОТОРНАЯ ЛОПАТКА (ВАРИАНТЫ) И ТУРБОУСТАНОВКА (57) Реферат: Роторная лопатка, имеющая платформу, функциями: Tmax=-0,8646*h+1,1087, Tmax=корневую часть, присоединенную к платформе, 1,0209*h+1,2058, Tmax=-0,7618*h+0,9985, где h и поверхность, оканчивающуюся в концевой процент от высоты лопатки. Толщина лопатки части и имеющую в поперечном сечении может быть приведена в соответствие с аэродинамическую форму. Толщина роторной эксплуатационными характеристиками лопатки изменяется в зависимости от ее высоты турбоустановки. Достигается оптимизация в соответствии с тремя различными линейными характеристик. 5 н. и 5 з.п. ф-лы, 1 табл, 5 ил. Стр.: 1 C 2 C 2 Адрес для переписки: 191036, Санкт-Петербург, а/я 24, "НЕВИНПАТ" 2 5 8 1 5 0 1 (56) Список документов, ...

Turbine blade aerodynamic profile (versions) and turbine (versions)

FIELD: engines and pumps. SUBSTANCE: turbine incorporates wheel rotor with multiple blades each comprising aerodynamic profile vane with designed profile corresponding, in fact, to values of Cartesian axials X, Y and Z listed in the table enclosed with the application materials. Z values are dimensionless quantities in the range of 0 to 1 transformed in distances Z expressed in inches by multiplying Z values by the vane height in inches. X and Y are distances in inches that, when conjugated by smooth continuous arcs, define the vane profile cross section at each Z distance. The profile cross sections at Z distances, when smoothly conjugated, form the vane complete shape. EFFECT: higher turbine efficiency. 20 cl, 9 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß RU (19) (11) 2 350 756 (13) C2 (51) ÌÏÊ F01D 5/14 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2004121998/06, 16.07.2004 (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 16.07.2004 (30) Êîíâåíöèîííûé ïðèîðèòåò: 18.07.2003 US 10/621,460 (73) Ïàòåíòîîáëàäàòåëü(è): ÄÆÅÍÅÐÀË ÝËÅÊÒÐÈÊ ÊÎÌÏÀÍÈ (US) (43) Äàòà ïóáëèêàöèè çà âêè: 20.01.2006 R U (72) Àâòîð(û): ÕÀÉÄ Ñóçàí Ìàðè (US), ÁÀÉ Ðîáåðò Ðîìàíè (US), ØÅÔÔÅÐ Äæîí Êîíðàä (US), ÑÈÌÑ Êàëâèí Ëåâè (US), ÁÎÉÑÊËÝÐ Ìàéêë Ýðíåñò (US) (45) Îïóáëèêîâàíî: 27.03.2009 Áþë. ¹ 9 2 3 5 0 7 5 6 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: US 6450770 Â1, 17.09.2002. ÅÐ 1231358 À2, 14.02.2002. ÅÐ 0887513 À2, 30.12.1998. US 4968246 À, 06.11.1990. US 2003/0017052 A1, 23.01.2003. SU 266475 À, 15.10.1975. SU 70723 À, 02.01.1946. C 2 (57) Ðåôåðàò: Òóðáèíà ñîäåðæèò ðàáî÷åå êîëåñî, èìåþùåå ìíîæåñòâî ëîïàòîê. Êàæäà èç ëîïàòîê âêëþ÷àåò â ñåá ëîïàñòü, èìåþùóþ ôîðìó àýðîäèíàìè÷åñêîãî ïðîôèë . Ëîïàñòü èìååò ðàñ÷åòíûé ïðîôèëü, ïî ñóùåñòâó ñîîòâåòñòâóþùèé çíà÷åíè ì äåêàðòîâûõ êîîðäèíàò X, Y è Z, ïðèâåäåííûì â òàáëèöå, ïðèâåäåííîé â ìàòåðèàëàõ çà âêè. Âåëè÷èíû Z âë þòñ áåçðàçìåðíûìè çíà÷åíè ìè â äèàïàçîíå îò 0 äî ...

Axial pump

1470832 Helico-centrifugal pumps ITT INDUSTRIES Inc 2 May 1974 [9 May 1973] 19306/74 Heading F1C In a pump, e.g. a submersible pump, comprising a housing containing a motor-driven impeller 5 and a stationary diffuser assembly 13, 14, the diameter Di of the impeller hub at its inlet end is between 40 and 80% of the maximum diameter D2 of the impeller, the angles between a plane normal to the impeller axis and the inlet and outlet edges of the impeller blades 9 are 10 to 30 degrees and 15 to 90 degrees respectively and the angles between the plane and the inlet and outlet edges of the diffuser blades 14 are 30 to 60 degrees and 75 to 105 degrees respectively. The impeller blades have substantially straight leading portions and curved trailing portions and define helical flow-paths. The inlet edges of the blades may be radial or backwardly curved and the radially outer edges 10 may be parallel to the impeller axis.

Automotive fan assembly with flared shroud and fan with conforming blade tips

자동차 엔진의 냉각 팬 조립체(10)에 있어서 고효율 및 저소음은 보호판 배럴(20)에 대하여 입구부(241)를 플레어형으로 하고 팬 블레이드(4)의 선단(46)을 상기 입구부의 형상에 일치하도록 성형함으로써 달성된다. 상기 블레이드 선단의 축방향 길이에 걸쳐 플레어형 입구부를 연장함으로써 상기 팬에 유입되는 유동 박리가 감소되고, 전체 블레이드 선단에 따른 재순환을 조절함으로써 선단 간극 손실이 감소된다. 블레이드 경사도를 이용하여 팬 편향을 최소화함으로써, 작은 선단 간격을 이용할 수 있데, 이것이 성능을 더욱 증대시킨다. The high efficiency and low noise in the cooling fan assembly 10 of the automobile engine is such that the inlet 241 is flared with respect to the shroud barrel 20 and the tip 46 of the fan blade 4 matches the shape of the inlet. By molding. Extending the flared inlet over the axial length of the blade tip reduces the flow separation into the fan and reduces the tip clearance loss by adjusting the recirculation along the entire blade tip. By minimizing fan deflection with blade tilt, small tip spacing can be used, which further increases performance.

Fan blade

The present invention employs improved fan blade shapes to improve fan blade performance in one or more manners (i.e., increased fan efficiency, lower fan noise, greater fluid moving capability, and the like). In some embodiments, the fan blade has a front side, a rear side, an inner attachment portion, an outer edge, a curved leading edge and a curved trailing edge. The outer edge can define an arc between a forward position and a rearward position of the fan blade. In some embodiments, the leading edge extends outward and intercepts the arc of the outer edge at the forward position, and the trailing edge extends outward to the rearward position. Various angles, lengths, and other dimensions of the blade can have selected values to produce superior fan performance.

Wind sail receptor

本发明涉及一种在风或水流中旋转的风帆接收器，其使轴旋转，该轴则使发电装置工作而产生电能输出，用于做功或者将电能输出传输到储存设备。优选的是，所述风帆接收器包括位于后轮毂和前盘之间的六到十片等距间隔开的相同叶片，后轮毂和前盘都与轴相连，该轴经由轴承安装到框架上，从而使得风帆接收器在面向风或水流时可以自由旋转。所述风帆接收器叶片由两组三至五片等距间隔开的叶片构成，每组由单片刚性材料的平展部分构成，从所述单片平展部分去除若干径向部分而形成围绕轮毂等距间隔开的各个叶片，将轮毂安装到彼此上，将叶片弯折成同样的曲形，并且叶片外端以相等的间距固定到前盘上，从而形成所述风帆接收器。

Axial fan

FIELD: engines and pumps. ^ SUBSTANCE: invention relates to axial pumps with vanes inclined in the fan rotation plane. Proposed fan revolves in direction (V) in plane (XY) about axis (2). It comprises central hub (3), multiple vanes (4), each comprising root (5) and head (6). Note here that vanes (4) are bounded by convex front edge (7) and concave rear edge (8). Note here that the said front edge (7) comprises the first circular arc segment, the closest to root (5), with its radius varying from 79% to 97% of the radius of head (6). It comprises also the second circular arc segment, closest to head (6) with its radius varying from 49.5% to 60.5% of the radius of head (6). Note here that the radius of transition between two aforesaid circular arc segments varies from 40% to 48.5% of the length of vane (4). ^ EFFECT: reduced noise. ^ 18 cl, 4 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 363 861 (13) C2 (51) МПК F04D 29/38 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21), (22) Заявка: 2007104343/06, 05.07.2005 (24) Дата начала отсчета срока действия патента: 05.07.2005 (73) Патентообладатель(и): СПАЛ АУТОМОТИВЕ С.р.Л. (IT) R U (30) Конвенционный приоритет: 06.07.2004 IT BO2004A000417 (72) Автор(ы): СПАДЖЬЯРИ Алессандро (IT) (43) Дата публикации заявки: 20.08.2008 2 3 6 3 8 6 1 (45) Опубликовано: 10.08.2009 Бюл. № 22 (56) Список документов, цитированных в отчете о поиске: US 6241474 A, 05.06.2001. EP 0945625 A, 29.09.1999. SU 985454 A1, 30.12.1982. RU 2188340 C1, 27.08.2002. RU 2208712 C2, 20.07.2003. JP 2000205190 A, 25.07.2000. 2 3 6 3 8 6 1 R U (86) Заявка PCT: IB 2005/001898 (05.07.2005) C 2 C 2 (85) Дата перевода заявки PCT на национальную фазу: 06.02.2007 (87) Публикация PCT: WO 2006/006043 (19.01.2006) Адрес для переписки: 129090, Москва, ул. Б.Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и Партнеры", пат.пов. С.А.Дорофееву, рег.№ 146 (54) ОСЕВОЙ ВЕНТИЛЯТОР (57) Реферат: ...

ROTOR FOR A GAS TURBINE.

PROFILES FOR FAIRED AERIAL BLADE

DIAGONAL FLOW FAN ROTOR WHOSE BLADES HAVE A DEVELOPABLE SURFACE

Rotor de ventilateur à flux diagonal dont les pales présentent une surface développable. Les pales d'un rotor d'un ventilateur à flux diagonal devraient présenter, pour prendre une forme idéale sur le plan de la mécanique des fluides, une surface torsadée à double courbure non développable. La forme des pales obtenue, par la combinaison d'une surface cylindrique et d'une surface plane tangente à la précédente ou par la combinaison de deux surfaces cylindriques tangentes, est celle d'une surface développable dont l'effet aérodynamique est très proche de l'idéalité. On utilise à cet effet des lignes d'intersection, soit d'une surface cylindrique et d'un plan, soit de deux surfaces cylindriques, avec un certain nombre de surfaces coniques coaxiales imaginaires représentant les lignes de flux du ventilateur. Circulation de propulsion de gaz et analogues. Diagonal flow fan rotor whose blades have a developable surface. The blades of a rotor of a diagonal flow fan should have, in order to assume an ideal shape from the point of view of fluid mechanics, a twisted, non-developable double curvature surface. The shape of the blades obtained, by the combination of a cylindrical surface and a plane surface tangent to the previous one or by the combination of two tangent cylindrical surfaces, is that of a developable surface whose aerodynamic effect is very close to ideality. Intersection lines, either of a cylindrical surface and a plane, or of two cylindrical surfaces, are used for this purpose, with a number of imaginary coaxial conical surfaces representing the flow lines of the fan. Gas propulsion circulation and the like.

Compressor turbine blade airfoil profile

A turbine blade includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 1. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

IMPROVEMENTS ON AIR PROPELLERS WITH REGARD TO THE PROFILE OF THEIR BLADES

Turbine wheel of exhaust gas turbocharger

BLADE PROFILE FOR AIRCRAFT ROTATING AIRCRAFT AND BLADE FOR ROTATING AIRCRAFT WITH SUCH A PROFILE

BLADE PROFILE FOR AN AIRCRAFT TURNING SAIL

PROFIL DE PALE POUR VOILURE TOURNANTE D'AERONEF, COMPORTANT ENTRE LE BORD D'ATTAQUE ET LE BORD DE FUITE UN EXTRADOS CONVEXE ET UN INTRADOS NON CONCAVE. CE PROFIL EST CARACTERISE EN CE QUE, AU POINT DE COURBURE MAXIMALE DE BORD D'ATTAQUE, LE RAYON DE COURBURE RO EST APPROXIMATIVEMENT DEFINI PAR L'EXPRESSION RO 1,7 C. E, DANS LAQUELLE C REPRESENTE LA CORDE ET E L'EPAISSEUR RELATIVE DUDIT PROFIL ET EN CE QUE LA PORTION D'INTRADOS VOISINE DU BORD D'ATTAQUE S'ETEND JUSQU'A ENVIRON 20 DE LA CORDE A PARTIR DUDIT BORD D'ATTAQUE ET PRESENTE UNE COURBURE GENERALE TRES FAIBLE DIMINUANT DE FACON CONTINUE EN DIRECTION DU BORD DE FUITE JUSQU'AU POINT DE COURBURE MINIMALE DE L'INTRADOS. OBTENTION DE VOILURES TOURNANTES, PAR EXEMPLE POUR HELICOPTERES, CAPABLES DE TRES HAUTES PERFORMANCES A LA FOIS EN VOL STATIONNAIRE ET EN VOL A GRANDE VITESSE, AINSI QU'EN EVOLUTIONS. BLADE PROFILE FOR AIRCRAFT ROTATING BLADES, INCLUDING BETWEEN THE ATTACKING EDGE AND THE TRAILING EDGE A CONVEX EXTRADOS AND A NON CONCAVE INTRADOS. THIS PROFILE IS CHARACTERIZED IN THAT, AT THE POINT OF MAXIMUM CURVATURE OF THE LEADING EDGE, THE RADIUS OF CURVATURE RO IS APPROXIMATELY DEFINED BY THE EXPRESSION RO 1.7 C. E, IN WHICH C REPRESENTS THE ROPE AND E THICKNESS RELATING TO THE SAID PROFILE AND IN THAT THE PORTION OF INTRADOS NEAR THE ATTACKING EDGE EXTENDS UP TO APPROXIMATELY 20 OF THE ROPE FROM THE SAID LEADING EDGE AND SHOWS A VERY LOW GENERAL CURVATURE STEADY REDUCING TOWARDS THE TRAILING EDGE TO THE MINIMUM CURVATURE POINT OF THE INTRADOS. OBTAINING ROTATING SAILS, FOR EXAMPLE FOR HELICOPTERS, CAPABLE OF VERY HIGH PERFORMANCE BOTH IN STATIONARY FLIGHT AND IN HIGH SPEED FLIGHT, AS WELL AS EVOLUTION.

A impeller structure of fuel pump

본 발명은 자동차용 연료펌프의 임펠러구조에 관한 것으로서, 각 임펠러챔버 내에서 연료 유입각도와 유출각도의 조절을 통해 고압 연료의 토출유량을 극대화시킬 수 있도록 하고, 연료펌프의 사용압력 고압화에 따른 임펠러의 성능을 향상시키기 위한 것이다. The present invention relates to an impeller structure of a fuel pump for an automobile, to maximize the discharge flow rate of the high pressure fuel by adjusting the fuel inlet angle and the outlet angle in each impeller chamber, according to the increase in the operating pressure of the fuel pump To improve the performance of the impeller. 이를 실현하기 위한 본 발명의 임펠러는, 원판 형상을 갖으며, 그 외측 둘레부의 원주방향을 따라 일정 간격으로 다수의 블레이드(11)가 소정의 경사면을 이루며 형성되었고, 상기 블레이드(11) 사이에는 고속 회전력에 의해 연료의 유입 및 유출이 이루어지는 임펠러 챔버(12)가 양면으로 관통 형성되어져 있는 통상의 연료펌프용 임펠러(10)에 있어서, 상기 각 임펠러 챔버(12)는 연료의 유입영역측에 해당하는 블레이드(11) 내측의 유입안내면(11a) 수직단면방향 각도(θ1)를 연료 유출영역측인 블레이드(11) 외측의 유출안내면(11b) 수직단면방향 각도(θ2)보다 크도록 구비한 것을 특징으로 한다. Impeller of the present invention for realizing this has a disk shape, a plurality of blades 11 are formed at a predetermined interval along a circumferential direction of the outer peripheral portion of the predetermined inclined surface, between the blades 11 at high speed In the conventional fuel pump impeller 10 in which the impeller chamber 12 through which the fuel flows in and out by the rotational force is formed on both sides, each impeller chamber 12 corresponds to the inflow region side of the fuel. It characterized in that the inlet guide surface (11a) vertical cross-sectional angle (θ1) inside the blade 11 is larger than the vertical cross-sectional angle (θ2) of the outflow guide surface (11b) outside the blade 11, which is the fuel outlet region side. do. 임펠러, 연료, 유입각, 유출각, 블레이드, 연료펌프 Impeller, fuel, inlet angle, outlet angle, blade, fuel pump

DAWN WITH NON AXISYMETRIC LINEAR PLATFORM.

BLADE PROFILE FOR AIRCRAFT ROTATING AIRCRAFT AND BLADE FOR ROTATING AIRCRAFT WITH SUCH A PROFILE

The invention concerns a blade profile for aircraft rotor, comprising, between a leading edge (1A) and a trailing edge (1B), a suction face (2) and a blade face (3) whereof the geometric locus of the equidistant points of the latter defines the curvature. The invention is characterised in that the value of the ratio of the maximum curvature to the maximum thickness develops linearly with the profile (1) relative thickness and ranges between 0.13 and 0.19 for a relative thickness of 7 % of the chord (C) and ranges between 0.18 and 0.24 for a relative thickness of 15 % of the chord (C).

Patent FR2228966A1

Patent FR2228966B1

Blade for rotating wing of helicopter is divided in three zones, with width of blade maximal in first zone, decreasing linearly in second one, and decreasing following parabolic function in third one

Blade (1) is subdivided in three zones (Z1, Z2, Z3) along its length. First zone (Z1) extends front inner edge (R0) to section situated at around 90% of its total length (R1); second zone (Z2) extends from section R1 to section situated at around 95 % of total length (R2); and third zone (Z3) extends from section R2 to free end (R) of blade. Width (L) is maximum, and slightly constant in first zone, decreases linearly in second zone, and decreases following parabolic function in third zone.

Airfoil shape for compressor

예시적인 실시예에 따른 장치, 시스템, 및 방법은, 작동 특성을 최적화시키기 위해 특정 형상을 갖는, 예를 들어, 터보 기계와 연계된 로터 또는 스테이터의 일부분으로서 블레이드를 제공한다. 다른 사항 중에서도, 블레이드 높이의 함수로 블레이드 두께가 터보 기계의 작동 특성에 맞게 맞춤화될 수 있다. The apparatus, system, and method according to exemplary embodiments provide a blade as a portion of a rotor or stator associated with a turbomachine, for example, having a particular shape to optimize operating characteristics. Among other things, blade thickness as a function of blade height can be tailored to the operating characteristics of the turbomachine.

PROFILES FOR AERIAL CARRIAGE BLADE

Profil 1 pour pale d'hélice aérienne carénée, dont l'épaisseur relative est comprise entre 9 % et 15 %. Selon l'invention, la courbure dudit profil ayant une valeur maximale au bord d'attaque A de celui-ci, la ligne d'extrados 2 comporte trois portions successives 2.1, 2.2 et 2.3 telles que : - dans la première portion 2.1, la courbure décroît rapidement de ladite valeur maximale au bord d'attaque à une valeur voisine de 20 en un premier point B dont l'abscisse réduite est voisine de 1 %; - dans la deuxième portion 2.2, la courbure décroît plus lentement de ladite valeur voisine de 20 audit premier point B jusqu'à une valeur voisine de 1 en un deuxième point D dont l'abscisse réduite est voisine de 25 %; et - dans la troisième portion 2.3, la courbure est inférieure à 1 entre ledit second point D et ledit bord de fuite C. Profile 1 for a streamlined air propeller blade, the relative thickness of which is between 9% and 15%. According to the invention, the curvature of said profile having a maximum value at the leading edge A thereof, the upper surface line 2 comprises three successive portions 2.1, 2.2 and 2.3 such that: - in the first portion 2.1, the curvature decreases rapidly from said maximum value at the leading edge to a value close to 20 at a first point B whose reduced abscissa is close to 1%; - in the second portion 2.2, the curvature decreases more slowly from said value close to 20 at said first point B to a value close to 1 at a second point D whose reduced abscissa is close to 25%; and - in the third portion 2.3, the curvature is less than 1 between said second point D and said trailing edge C.

HIGH PERFORMANCE BLADE FOR HELICOPTER ROTOR

PALE A HAUTES PERFORMANCES POUR ROTOR D'HELICOPTERE PRESENTANT UNE SURFACE AERODYNAMIQUE 9 ENGENDREE PAR DES PROFILS DONT LE VRILLAGE AERODYNAMIQUE AUGMENTE DEPUIS LE PROFIL D'EXTREMITE 7 VERS LE PROFIL D'EMPLANTURE 8 POUR ENSUITE ETRE INVERSE ET DEVENIR NUL AUX ATTACHES 3 DE LA PALE. SELON L'INVENTION, L'ANGLE DE VRILLAGE, FORME PAR LA CORDE DE PORTANCE NULLE C D'UN PROFIL DE LA SURFACE AERODYNAMIQUE 9 ET UN PLAN DE REFERENCE P PASSANT PAR LE MILIEU DES ATTACHES 3 DE LA PALE 1 AU MOYEU DU ROTOR, EST POUR LE PROFIL D'EXTREMITE 7 AU PLUS EGAL A UNE VALEUR TH DE 0,3DEGRE. OBTENTION DE VOILURES TOURNANTES, PAR EXEMPLE POUR HELICOPTERES, CAPABLES DE TRES HAUTES PERFORMANCES, NOTAMMENT EN VOL D'AVANCEMENT RAPIDE SOUS FORTE CHARGE. HIGH PERFORMANCE BLADE FOR HELICOPTER ROTOR WITH AN AERODYNAMIC SURFACE 9 GENERATED BY PROFILES WHOSE AERODYNAMIC TWISTING INCREASES FROM END PROFILE 7 TOWARDS SOCKET PROFILE 8 TO THEN BE REVERSE AT PTACHES 3 AND BECOME NULL . ACCORDING TO THE INVENTION, THE TURNING ANGLE, FORMED BY THE ZERO LIFT ROPE C OF A PROFILE OF THE AERODYNAMIC SURFACE 9 AND A REFERENCE PLANE PASSING THROUGH THE MIDDLE OF THE FASTENERS 3 OF THE BLADE 1 THROUGH THE ROTOR, IS FOR THE END PROFILE 7 AT THE MOST EQUAL TO A TH VALUE OF 0.3DEGRE. OBTAINING ROTATING SAILS, FOR EXAMPLE FOR HELICOPTERS, CAPABLE OF VERY HIGH PERFORMANCE, ESPECIALLY IN FAST FORWARD FLIGHT UNDER HEAVY LOAD.

Patent FR2536365B1

FRANCIS-TYPE WHEEL AND HYDRAULIC MACHINE EQUIPPED WITH SUCH A WHEEL

Francis wheel for hydraulic machine has blade angle between linear velocity and median line at trailing edge of 20 - 25 deg.

The Francis wheel, having a top, a ring and a series of blades (2) between them forming liquid flow ducts, has the angle between the linear velocity (U) of a blade's movement and the median line (25) of the blade at the level of its trailing edge close to the point (224) where the blade joins the ring is between 20 and 25 degrees. At the blade's leading edge the angle between the linear velocity and median line has a mean value of between 70 and 120 degrees.

ROTOR FOR A GAS TURBINE.

L'INVENTION CONCERNE UN ROTOR POUR UNE TURBINE A GAZ. LE ROTOR COMPORTE DES AUBES4 INCURVEES SPATIALEMENT ET DONT LA COURBURE EST ORIENTEE, DANS UNE ZONE A BALAYAGE RADIAL, EN SENS OPPOSE AU SENS DE ROTATION DU ROTOR; LES AUBES4 SONT DISPOSEES SUR UN MOYEU POURVU D'UNE ZONE EXTREME EN FORME DE DISQUE; POUR OBTENIR UNE FORME D'AUBE FAVORABLE POUR L'ECOULEMENT TOUT EN REDUISANT SIMULTANEMENT LE MOMENT D'INERTIE DU ROTOR, LES AUBES COMPORTENT, LE LONG DE LEUR ETENDUE AXIALE, DES LIGNES DE SQUELETTE11 QUI SONT ORIENTEES DANS UNE DIRECTION RADIALE ENTRE LES PARTIES DU CONTOUR DES AUBES QUI SONT PLACEES DU COTE D'ENTREE ET DU COTE DE SORTIE DE L'ECOULEMENT, LESDITES LIGNES DE SQUELETTE11 POUVANT ETRE DEFINIES PAR UNE COURBE DU SECOND DEGRE, TELLE QU'UNE ELLIPSE. APPLICATION AUX TURBOCOMPRESSEURS. THE INVENTION RELATES TO A ROTOR FOR A GAS TURBINE. THE ROTOR INCLUDES SPATIALLY CURVED BLADES4 WHOSE CURVATURE IS ORIENTED, IN A RADIAL SCAN ZONE, OPPOSITE THE DIRECTION OF ROTATION OF THE ROTOR; THE BLADES4 ARE ARRANGED ON A HUB PROVIDED WITH AN EXTREME DISC-SHAPED ZONE; TO OBTAIN A FAVORABLE DAWN SHAPE FOR FLOWING WHILE SIMULTANEOUSLY REDUCING THE MOMENT OF INERTIA OF THE ROTOR, THE BLADES HAVE, ALONG THEIR AXIAL EXTENT, SKELETON LINES11 WHICH ARE ORIENTED IN A RADIAL DIRECTION BETWEEN THE PARTS OF THE ROTOR. CONTOUR OF THE BLADES WHICH ARE PLACED ON THE ENTRY SIDE AND ON THE EXIT SIDE OF THE FLOW, THE SAID SKELETON LINES11 CAN BE DEFINED BY A SECOND DEGREE CURVE, SUCH AS AN ELLIPSE. APPLICATION TO TURBOCOMPRESSORS.

BLADE FOR AN AIRCRAFT ROTATING VESSEL AND ROTARY VAULT COMPRISING SUCH A BLADE

Selon l'invention, ladite pale est survrillée dans la zone d'extrémité à partir d'au moins 0,85 R de façon que le vrillage résultant soit au moins égal à un vrillage limite thetalimC dépendant de la forme en plan Co/C(r) de ladite pale dans cette zone et de telle sorte que le coefficient de portance Cz ait, dans une première fraction de la zone d'extrémité, s'étendant au moins entre r = 0,85 R et r = 0,9 R une valeur décroissante en restant inférieure à une première valeur limite Czlim1 = Czm - a(r/R - b), Czm étant le coefficient de portance moyen de ladite voilure tournante et a et b des constantes expérimentales, et dans une seconde fraction d'extrémité s'étendant entre r = 0,9 R et au moins r = 0,95 R, le coefficient de portance continue sa décroissance en restant inférieur ou égal à une seconde valeur limite Czlim2 décroissant linéairement de la valeur Czlim1 pour r = 0,9R jusqu'à la valeur zéro pour r = R. According to the invention, said blade is oversized in the end zone from at least 0.85 R so that the resulting twist is at least equal to a limit twist thetalimC depending on the shape in the Co / C plane ( r) of said blade in this zone and such that the coefficient of lift Cz has, in a first fraction of the end zone, extending at least between r = 0.85 R and r = 0.9 R a decreasing value while remaining lower than a first limit value Czlim1 = Czm - a (r / R - b), Czm being the average lift coefficient of said rotary wing and a and b experimental constants, and in a second fraction of end extending between r = 0.9 R and at least r = 0.95 R, the lift coefficient continues its decrease while remaining less than or equal to a second limit value Czlim2 decreasing linearly from the value Czlim1 for r = 0, 9R to zero for r = R.

PROCESS FOR REALIZING PROPELLER BLADES AND IMPROVED PROPELLER BLADES OBTAINED BY IMPLEMENTING THIS PROCESS

BLADE FOR AIRCRAFT PROPELLER

LA PARTIE EXTERNE AU MOINS D'UNE PALE D'HELICE, PRESENTANT UNE EPAISSEUR RELATIVE MAXIMALE COMPRISE ENTRE ENVIRON 2 ET 6, A UN PROFIL DONT LA LOI DE VARIATION D'EPAISSEUR LE LONG DE LA CORDE COMPORTE UNE PREMIERE ZONE I ALLANT DU BORD D'ATTAQUE JUSQU'A ENVIRON 8 DE LA LONGUEUR DE LA CORDE DANS LAQUELLE LA COURBURE DECROIT RAPIDEMENT, DEPUIS UNE VALEUR MAXIMUM AU BORD D'ATTAQUE, SUIVIE D'UNE SECONDE ZONE II S'ETENDANT ENTRE ENVIRON 8 DE LA CORDE ET LE MAITRE COUPLE DANS LAQUELLE LA COURBURE DECROIT LINEAIREMENT. DANS UNE TROISIEME ZONE, S'ETENDANT DU MAITRE COUPLE JUSQU'A 75 A 85 DE LA CORDE, LA COURBURE EST SENSIBLEMENT CONSTANTE. UNE QUATRIEME ZONE IV, S'ETENDANT DE LA FIN DE LA TROISIEME ZONE TYPIQUEMENT A 80 DE LA CORDE AU BORD DE FUITE, COMPORTE UNE INVERSION DE COURBURE. THE EXTERNAL PART OF AT LEAST ONE PROPELLER BLADE, WITH A MAXIMUM RELATIVE THICKNESS BETWEEN APPROXIMATELY 2 AND 6, HAS A PROFILE WHOSE LAW OF THICKNESS VARIATION ALONG THE ROPE INCLUDES A FIRST ZONE I GOING FROM THE EDGE 'ATTACK UP TO ABOUT 8 OF THE ROPE LENGTH IN WHICH THE BEND DECREASES RAPIDLY, FROM MAXIMUM VALUE AT THE ATTACKING EDGE, FOLLOWED BY A SECOND ZONE II EXTENDING ABOUT 8 OF THE ROPE AND THE MASTER TORQUE IN WHICH THE CURVATURE DECREASES LINEARLY. IN A THIRD ZONE, EXTENDING FROM THE MASTER TORQUE UP TO 75-85 OF THE ROPE, THE CURVATURE IS SENSITIVELY CONSTANT. A FOURTH ZONE IV, EXTENDING FROM THE END OF THE THIRD ZONE TYPICALLY 80 FROM THE ROPE TO THE TRAILING EDGE, IS INVERT OF CURVATURE.

AIRCRAFT TURNING BLADE

Airfoil profile for aircraft

Profil de voilure pour vol à vitesses subsoniques élevées,du type comportant un extrados convexe plat, un bord d'attaque épais et un intrados convexe vers le bord d'attaque et concave vers le bord de fuite. Selon l'invention, ce profil est caractérisé en ce que l'extrados comporte un maximum de courbure au voisinage de sa partie arrière, dans une zone délimitée par des points situés à des distances du bord d'attaque égales à 65 et 90 % de la corde du profil. Réalisation de voilures fixes ou tournantes pour aéronef, présentant un Mach de divergence élevé et une faible traînée.

Hp turbine vane airfoil profile

A high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The design of the airfoil equalizes the static pressure gradient in the spanwise direction. This allows to minimize secondary losses.

CARRYING SURFACE SECTION FOR A ROTOR BLADE OF A GIRAVION

L'INVENTION CONCERNE UNE SECTION DE SURFACE PORTANTE POUR UNE PALE DE ROTOR D'UN GIRAVION. L'EXTRADOS ET L'INTRADOS DE LA SECTION DE SURFACE PORTANTE 22 DE LA PALE DE ROTOR 14 SONT PROFILES PAR UNE REPARTITION D'EPAISSEUR ET UNE REPARTITION DE CAMBRURE ETUDIEES DE TELLE SORTE QUE LEUR COURBURE SOIT CONSTANTE OU CHANGE A UNE ALLURE CONSTANTE SUR CERTAINES ZONES DE LA SURFACE PORTANTE22. L'INVENTION EST UTILISEE DANS LES PALES DE ROTORS DE GIRAVIONS POUR EVITER LA FORMATION DE FORTES ONDES DE CHOC NORMALES A DES NOMBRES DE MACH LOCAUX INFERIEURS A 1,2 LORS D'UN VOL HORIZONTAL DANS DES CONDITIONS DE TEMPERATURE ET DE PRESSION NORMALES. THE INVENTION RELATES TO A STRUCTURAL SURFACE SECTION FOR A ROTOR BLADE OF A GIRAVION. THE EXTRADOS AND THE INTRADOS OF THE LOADING SURFACE SECTION 22 OF THE ROTOR BLADE 14 ARE PROFILED BY A THICKNESS DISTRIBUTION AND A CAMBER DISTRIBUTION OF SUCH KIND THAT THEIR CURVATURE IS CONSTANT OR CHANGES TO A CONSTANT APPEARANCE ON SOME LOADING SURFACE AREAS 22. THE INVENTION IS USED IN THE ROTOR BLADES OF GIRAVIONS TO AVOID THE FORMATION OF STRONG SHOCK WAVES NORMAL TO LOCAL MACH NUMBERS LESS THAN 1.2 DURING HORIZONTAL FLIGHT UNDER NORMAL TEMPERATURE AND PRESSURE CONDITIONS.

Apparatus and method for generating power from moving water

Apparatus (100) for generating power from a water current in a body of water comprises a longitudinally extending flotation platform (10) for maintaining the apparatus afloat in the body of water and a water turbine (101) operatively carried by the platform (10) for generating power in response to water current in the body of water. The platform (10) is configured to enhan ce the flow of water current over the turbine blades (120) and, as well, to enable a number of like platforms each with an associated turbine or turbine s to be arrayed in a cooperative manner. The water turbine may comprise a turbine rotor with a plurality of relatively narrow, flexible elongated blad es (120) arranged in circumferentially spaced rows extending along the rotor. I n each row, the blades are distanced from each other in succession by a space. The rows may be staggered with respect to each other such that the blades in a given one of the rows circumferentially align with the spaces between blades in the row immediately circumferentially forward of the given row and with t he spaces between blades in the row immediately circumferentially rearward of t he given row.

Patent FR2396191B1

Airfoil shape for arrays of airfoils

An Airfoil Shape for Arrays of Transonic Airfoils Abstract A flow directing assembly 14 having an airfoil section or shape 28 of the type adapted for use in an axial flow gas turbine engine is disclosed. The cambered meanline MCL of the airfoil shape is formed of a front circular arc FA and a rear circular arc RA. A thickness distribution TD is applied to the meanline to form the convex suction surface 20 and the concave pressure surface 22. The airfoil section exhibits good aerodynamic performance as compared with an equivalent circular arc airfoil in a transonic flow field. method for making the airfoil shape is disclosed. The method includes the steps of: forming a cambered mean-line of two circular arcs; forming a thickness distri-bution about the conical chord line Bt; and applying thickness distribution to the cambered meanline such that a portion of the suction surface is stretched and a portion of the pressure surface is compressed. .

Wind sail receptor

윈드 세일 리셉터는 전력 발생 장치를 작동시키기 위해 축을 회전시키며, 바람 또는 물의 흐름 내에서 회전하며, 상기 전력 발생 장치는 전력을 저장 장치로 이송시키기 위해 제공되거나 또는 작업을 수행하기 위해 전력을 발생시킨다. 바람직하게 윈드 세일 리셉터는 후방 허브와 전방 디스크 사이에 6개 내지 10개의 동일하게 이격된 블레이드를 포함하며, 상기 후방 허브와 전방 디스크는 베어링을 통해 프레임에 장착되는 축에 연결되고, 이에 따라 윈드 세일 리셉터는 바람 또는 물의 흐름으로 향할 때 자유롭게 회전할 수 있다. 상기 윈드 세일 리셉터의 블레이드는 3개 내지 5개의 동일하게 이격된 블레이드의 2개의 섹션으로 형성되며, 각각의 섹션은 강성의 재료의 단일 평평한 섹션으로 형성되고, 반경방향 섹션은 허브 주위에서 동일하게 이격된 각각의 블레이드를 형성하기 위해 제거되며, 상기 섹션의 허브들은 서로 끼워 맞춤되고, 블레이드는 곡선과 같이 만곡되며, 외측 블레이드의 단부들은 전방 디스크로 동일한 간격으로 고정되어 윈드 세일 리셉터가 형성된다. The wind sail receptor rotates the shaft to operate the power generating device and rotates in the flow of wind or water, which is provided to transfer power to the storage device or generates power to perform work. Preferably the wind sail receptor comprises six to ten equally spaced blades between the rear hub and the front disc, wherein the rear hub and the front disc are connected to an axis which is mounted to the frame via a bearing, thus the wind sail The receptor can rotate freely as it is directed to wind or water flow. The blades of the wind sail receptor are formed from two sections of three to five equally spaced blades, each section formed from a single flat section of rigid material, and the radial sections are equally spaced around the hub. Removed to form each of the blades, the hubs of the sections fit together, the blades curve like curves, and the ends of the outer blades are fixed at equal intervals with the front disk to form a wind sail receptor.

Housing for a centrifugal fan, pump or turbine

GAS TURBINE ENGINE

PROPELLER.

Stator vane profile optimization

一种用于定子叶片(40)的翼面件(60)，翼面件具有大致按照表I中设定的只有四个小数位的X、Y和Z的笛卡儿坐标值的未涂层型面，其中Z是离开安装有翼面件的平台(62)的距离，并且X和Y是在离开平台的每个距离Z处限定该型面的坐标。

Compressor turbine blade airfoil profile

A compressor turbine includes a series of compressor turbine blades each having an airfoil with a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

Wind turbine

A wind turbine has a shaft rotatable about an axis, and a plurality of blades mounted on the shaft and arranged to be rotated by wind and thereby rotate the shaft, wherein each of the blades has an outer portion which has an outer edge formed at the outer end of a radius with a center at the axis of the shaft and extends rearwardly from the outer edge over a circumference described from the center, and each of the blades has an inner edge which is rearwardly offset relative to the outer edge in a direction which is normal to the radius.

Airfoiled blade for cargo transport aircraft

An airfoiled blade is disclosed which comprises a plurality of airfoil sections, a root portion, and a tip portion. Each section has along substantially the entire length thereof a cross-sectional airfoil shape characterized by a parabolic leading edge, a front loading and a blunt trailing edge. Each of the airfoil sections has a chord passing therethrough with a 50% point and a maximum thickness forward of the 50% point, toward the leading edge. A thickness ratio range from a first of the airfoil sections nearest the tip portion to a last of the airfoil sections nearest the root portion of substantially 3% to 28% is preferred. In one embodiment, the blade further includes a second airfoil section, a third airfoil section and a fourth airfoil section located between the first and last airfoil sections. The first airfoil section has a thickness ratio of substantially 3.3%, the second airfoil section has a thickness ratio of substantially 4.1%, the airfoil section has a thickness ratio of substantially 7.3%, the fourth airfoil section has a thickness ratio of substantially 14.3%, and the last airfoil section has a thickness ratio of substantially 27.4%.

High efficiency rotor for the second phase of a gas turbine

Propeller blade of aircraft

Изобретение относитс  к авиационной технике, в частности к воздушным винтам летательных аппаратов, и касаетс  дальнейшего совершенствовани  аэродинамики лопастей Целью изобретени   вл етс  улучшение экс- плуатационных характеристик воздушных винтов летательных аппаратов путем задержки образовани  ударных волн и отрыва пограничного сло  при увеличении относительных чисел Маха. ЛоИзобретение относитс  к авиационной технике, в частности к воздушным винтам летательных аппаратов и ка- cajsrcfl дальнейшего совершенствовани  аэродинамики лопастей винтов. Развитие воздушных винтов св зано с их непрерывным совершенствованием с Целью повышени  КПД, уменьшени  шума, который  вл етс  пр мой функпасть воздушного винта имеет аэродинамический профиль, относительна  толщина которого составл ет 3 25%, образованный верхним выпуклым и нижним выпукло-вогнутым контурами. При максимальной величине на передней кромке кривизна верхнего,выпуклого контура профил  измен етс  монотонно, убыва  к задней кромке, достига  величины 4 на k% хорды и 0 на задней, кромке профил . Кривизна нижнего выпукло-вогнутого профил  также измен етс  монотонно, убыва  в направлении к задней кромке, причем от передней кромки она вначале убывает быстро , достига  величины 8 примерно на 3,5% хорды и далее убывает медленно до нулевой величины в точке, наход щейс  в диапазоне 10 - 60% хорды и далее монотонно убывает до отрицательной величины, остава сь практически посто нной у задней кромки. Законы изменени  кривизны профилей дл  различных толщин определены математическими зависимост ми и табличными данными в пр моугольной системе координат. 12 э.п. ф-лы, 16 ил., 4 табл. циеи относительной скорости на конце лопасти, снижени  массы лопастей, что может быть достигнуто путем сокращени  длин хорд профилей участков лопастей . Наблюдаетс  также стремление к созданию таких профилей лопастей, которые имеют высокие коэффициенты J сЈ о 00 CJ The invention relates to aeronautical engineering, in particular, to aircraft ...

Airfoil shape for a compressor

本发明公开了一种用于压缩机的翼型形状。带有该翼型形状的制造物品具有主要根据表1中列出的X、Y和Z的笛卡尔坐标值的标称型面。其中，X和Y为当由平滑连续的弧连接时在每个Z英寸距离处限定翼型型面截面的英寸距离。在Z距离处该型面截面彼此平滑地连接，以便形成整个翼型形状(22，23)。

High-performance blade for helicopter rotor

Pale à hautes performances pour rotor d'hélicoptère présentant une surface aérodynamique (9) engendrée par des profils dont le vrillage aérodynamique augmente depuis le profil d'extrémité (7) vers le profil d'emplanture (8) pour ensuite être inversé et devenir nul aux attaches (3) de la pale. Selon l'invention, l'angle de vrillage, formé par la corde de portance nulle C0 d'un profil de la surface aérodynamique (9) et un plan de référence P passant par le milieu des attaches (3) de la paie (1) au moyeu du rotor, est pour le profil d'extrémité (7) au plus égal à une valeur 01 de 0,3 degré. Obtention de voilures tournantes, par exemple pour hélicoptères, capables de très hautes performances, notamment en vol d'avancement rapide sous forte charge. High performance blade for helicopter rotor having an aerodynamic surface (9) generated by profiles whose aerodynamic twist increases from the end profile (7) towards the root profile (8) to then be inverted and become zero to the blade attachments (3). According to the invention, the twist angle, formed by the zero lift rope C0 of a profile of the aerodynamic surface (9) and a reference plane P passing through the middle of the fasteners (3) of the pay (1 ) at the rotor hub, is for the end profile (7) at most equal to a value 01 of 0.3 degrees. Obtaining rotary wings, for example for helicopters, capable of very high performance, especially in fast forward flight under heavy load.

Siroco fan

a sirocco fan body; a single wing and camber line which are formed on the fan body and satisfy the equations and, wherein the vertical thickness distribution about the tangent line at any point of the camber line satisfies the equation. In and, yc is a y coordinate of the camber line, m is a maximum vertical coordinate of the camber line, p is a site on the chord of the maximum vertical coordinate, and x is a horizontal coordinate on the chord. In, yt is a vertical thickness coordinate with respective to the tangent line at the site of -x, and t is a maximum thickness.