专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明专利

CA3010385A1 SHIELD FOR A TURBINE ENGINE AIRFOIL 未知
公开(公告)号：CA3010385A1
公开(公告)日：2019-01-19
申请号：CA3010385
申请日：2018-07-04
申请人： GEN ELECTRIC
发明人： MANNING ROBERT FRANCIS , BROOMER MARK , CORSETTI BRIAN KENNETH
IPC分类号： F01D5/14 , F01D25/12 , F02C7/12
摘要： An airfoil for a turbine engine can include a body having an outer wall defining a pressure side and a suction side, and the body can extend axially between a truncated nose and a trailing edge. A shield can be positioned upstream of the nose to define a leading edge for the airfoil.

2. 发明专利

CA2772384C CONTINUOUS RING COMPOSITE TURBINE SHROUD 未知
公开(公告)号：CA2772384C
公开(公告)日：2018-10-23
申请号：CA2772384
申请日：2012-03-22
申请人： GEN ELECTRIC
发明人： SHAPIRO JASON DAVID , BUHLER JARED PETER , CORSETTI BRIAN KENNETH
IPC分类号： F01D9/02 , F01D9/04
摘要： A composite annular shroud (42) supported by a support assembly (46) including at least two single piece full 360 degree rings (50, 52, 54 or 130) and at least partially disposed within an innermost one of the rings. The shroud (42) is biased against and in sealing engagement with an inner flange (84) of the innermost ring. A three ring assembly includes the inner ring (50) disposed radially inwardly of a middle ring (52) disposed radially inwardly of an outer ring (54) and the shroud (42) at least partially disposed within the inner ring (50). At least three clocking pins (74) extend radially inwardly from the middle ring (52) through slots (76) in the inner ring (50) into notches (78) in the shroud (42). The middle ring (52) may be an aft end (70) of a support ring (68) fixedly connected to an engine backbone (58). Mounting pins (104) may be press fitted into pin holes (106) in the middle ring (52) and extend radially outwardly from the middle ring (52) through radial holes (107) in the outer ring (54).

3. 发明专利

CA2772384A1 CONTINUOUS RING COMPOSITE TURBINE SHROUD 未知
公开(公告)号：CA2772384A1
公开(公告)日：2012-09-30
申请号：CA2772384
申请日：2012-03-22
申请人： GEN ELECTRIC
发明人： SHAPIRO JASON DAVID , BUHLER JARED PETER , CORSETTI BRIAN KENNETH
IPC分类号： F01D9/02 , F01D9/04
摘要： A composite annular shroud (42) supported by a support assembly (46) including at least two single piece full 360 degree rings (50, 52, 54 or 130) and at least partially disposed within an innermost one of the rings. The shroud (42) is biased against and in sealing engagement with an inner flange (84) of the innermost ring. A three ring assembly includes the inner ring (50) disposed radially inwardly of a middle ring (52) disposed radially inwardly of an outer ring (54) and the shroud (42) at least partially disposed within the inner ring (50). At least three clocking pins (74) extend radially inwardly from the middle ring (52) through slots (76) in the inner ring (50) into notches (78) in the shroud (42). The middle ring (52) may be an aft end (70) of a support ring (68) fixedly connected to an engine backbone (58). Mounting pins (104) may be press fitted into pin holes (106) in the middle ring (52) and extend radially outwardly from the middle ring (52) through radial holes (107) in the outer ring (54).

4. 发明专利

CA2949297A1 FILLET OPTIMIZATION FOR TURBINE AIRFOIL 未知
公开(公告)号：CA2949297A1
公开(公告)日：2017-06-07
申请号：CA2949297
申请日：2016-11-22
申请人： GEN ELECTRIC
发明人： BUHLER JARED PETER , BUNKER RONALD SCOTT , CORREIA VICTOR HUGO SILVA , CORSETTI BRIAN KENNETH
IPC分类号： F01D5/18 , F01D25/12
摘要： A blade for a gas turbine engine (10) comprises an airfoil (78) having a pressure side (98) and a suction side (100), with a root (82) and a tip wall (120). The pressure side (98) and suction side (100) extend beyond the tip wall (120) to define a tip channel (121), defining a plurality of internal and external corners (138). The corners (138) comprise fillets (140) to define a thickness being greater than the thickness for the pressure (98), suction (100), or tip walls (120). A film hole (132) can extend through the fillet (140), such that the length of the film hole (132) at the fillet (140) can be increased to define an increased length-to-diameter ratio for the film hole (132) to improve film cooling through the film hole (132).

5. 发明专利

CA2928177A1 TURBINE BAND ANTI-CHORDING FLANGES 未知
公开(公告)号：CA2928177A1
公开(公告)日：2016-11-07
申请号：CA2928177
申请日：2016-04-28
申请人： GEN ELECTRIC
发明人： CORREIA VICTOR HUGO SILVA , CORSETTI BRIAN KENNETH , BROOMER MARK
IPC分类号： F01D9/02 , F01D25/10
摘要： A gas turbine engine arcuate segment includes arcuate flange with anti-chording means extending away from annular wall. Anti-chording means may include insert in or bonded to flange and made of different alpha material than the annular wall. Anti-chording means may be heating means for heating flange. Heating means includes hot air inlet to and an outlet from a circumferentially extending heating flow passage embedded in flange and may further include a cold air inlet to heating flow passage. Heating flow passage may be a serpentine heating flow passage with an undulating heating flowpath. A turbine nozzle segment includes one or more airfoils extending radially between inner and outer arcuate band segments and forward and aft outer flanges extending radially from the outer arcuate band segment include anti-chording means. An arcuate turbine shroud segment includes forward and aft shroud rail segments with anti-chording means.

6. 发明专利

CA2949271A1 GAS TURBINE ENGINE WITH FILLET FILM HOLES 未知
公开(公告)号：CA2949271A1
公开(公告)日：2017-06-07
申请号：CA2949271
申请日：2016-11-22
申请人： GEN ELECTRIC
发明人： BUHLER JARED PETER , BUNKER RONALD SCOTT , CORREIA VICTOR HUGO SILVA , CORSETTI BRIAN KENNETH
IPC分类号： F01D5/18 , F01D25/12
摘要： An airfoil for a gas turbine engine can have an exterior wall and an interior wall, with each wall having a thickness. The walls can intersect to define a corner at the intersection. A cooling passage can be defined by the walls at or near the corner to provide fluid communication between the interior and exterior of the airfoil. A film hole can be disposed in the walls and can have a length and diameter to define a ratio of length to diameter, L/D. An arcuate fillet can be located in the corner to define an effective radius for the fillet. The effective radius can be at least 1.5 times larger than the thicknesses of the walls to provide for an increased length to diameter ratio for the film hole.

7. 发明专利

BR102016009271A2 segmento arqueado de motor de turbina a gás e bico de turbina 未知
公开(公告)号：BR102016009271A2
公开(公告)日：2016-11-16
申请号：BR102016009271
申请日：2016-04-26
申请人： GEN ELECTRIC
发明人： CORSETTI BRIAN KENNETH , BROOMER MARK , CORREIA VICTOR HUGO SILVA
IPC分类号： F01D25/00
摘要： a presente invenção se refere a um segmento arqueado de motor de turbina a gás (33) que inclui um flange arqueado (72) com meio antiencurvamento (60) que se estende para longe da parede anular (38). o meio antiencurvamento (60) pode incluir uma inserção (110) em ou ligada ao flange (72) e feita de material de alfa diferente do que a parede anular (38). o meio antiencurvamento (60) pode ser um meio de aquecimento (112) para aquecer o flange (72). o meio de aquecimento (112) inclui entrada de ar quente (115) para e uma saída (126) a partir de uma passagem de fluxo de aquecimento que se estende circunferencialmente (116) embutida no flange (72) e pode adicionalmente incluir uma entrada de ar frio (132) para a passagem de fluxo de aquecimento (116). a passagem de fluxo de aquecimento (116) pode ser uma passagem de fluxo de aquecimento em serpentina (138) com um trajeto de fluxo de aquecimento ondulado (137). um segmento de bico de turbina (32) inclui um ou mais aerofólios (34) que se estendem radialmente entre os segmentos de banda arqueados interno e externo (37, 38) e os flanges externos dianteiro e traseiro (70, 72) que se estendem radialmente a partir do segmento de banda arqueado externo (38) incluem o meio antiencurvamento (60). um segmento de reforço de turbina arqueado (40) inclui os segmentos de trilho de reforço dianteiro e traseiro (80, 82) com o meio antiencurvamento (60).

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式