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1. 发明授权

US5353586A Combustion chamber assembly with hollow support strut for carrying cooling air 失效
标题翻译：具有中空支撑支柱的燃烧室组件，用于承载冷却空气
公开(公告)号：US5353586A
公开(公告)日：1994-10-11
申请号：US122595
申请日：1993-10-01
申请人： David H. Taylor , Arthur B. Griffin
发明人： David H. Taylor , Arthur B. Griffin
IPC分类号： F02C7/20 , F23R3/60 , F02C3/14
CPC分类号： F02C7/20 , F23R3/60
摘要： The smaller diameter end of a first stiff frustoconical casing member (74) is secured to a compressor casing (34) and the smaller diameter end of a second stiff frustoconical casing member (80) is secured to the nozzle guide vanes (40). A plurality of hollow axially extending members (86) are secured to the first and second stiff frustoconical members (74, 80) to transfer tensile and compressive stresses between the compressor casing (34) and the nozzle guide vanes (40). The larger diameter end of the first stiff frustoconical member (74) is secured to an engine casing (52) by a first radially and axially flexible member (88) to define a second chamber (100), and the larger diameter end of the second stiff frustoconical member (80) is secured to the engine casing (52) by a second radially and axially flexible member (94) to define a third chamber (102). The hollow axially extending members (86) define passages (104) to allow cooling air to flow from the first chamber (100) through the second chamber (102) to a turbine. The axially extending members (86) pass circumferentially between adjacent tubular combustion chambers (42) which have their axes arranged radially.
摘要翻译： PCT No.PCT / GB92 / 00017 Sec。 371日期：1993年10月1日 102（e）日期1993年10月1日PCT提交1992年1月6日PCT公布。公开号WO92 / 18760 日期为1992年10月29日。第一刚性截头圆锥形壳体构件（74）的较小直径端固定到压缩机壳体（34），并且第二刚性截头圆锥形壳体构件（80）的较小直径端固定到喷嘴导叶（40）。多个中空的轴向延伸构件（86）固定到第一和第二刚性截头圆锥构件（74,80），以在压缩机壳体34和喷嘴导向叶片40之间转移拉伸和压缩应力。第一刚性截头圆锥形构件（74）的较大直径的端部通过第一径向和轴向柔性构件（88）固定到发动机壳体（52），以限定第二室（100），并且第二刚性的截头圆锥形构件（80）通过第二径向和轴向柔性构件（94）固定到发动机壳体（52），以限定第三室（102）。空心轴向延伸构件（86）限定通道（104），以允许冷却空气从第一室（100）通过第二室（102）流动到涡轮机。轴向延伸构件（86）周向地在相邻的管状燃烧室（42）之间通过，这些管状燃烧室的轴线径向布置。

2. 发明授权

US5470198A Sealing structures for gas turbine engines 失效
标题翻译：燃气轮机发动机密封结构
公开(公告)号：US5470198A
公开(公告)日：1995-11-28
申请号：US299061
申请日：1994-08-31
申请人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
发明人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
IPC分类号： F01D9/02 , F01D9/04 , F01D11/00 , F02C7/00 , F02C7/28 , F01D5/18
CPC分类号： F01D9/023 , F01D11/005 , Y02T50/671 , Y02T50/675
摘要： A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly extending between nozzle guide vanes and combustion chamber discharge nozzles. The nozzle guide vanes have platforms having extensions which in one embodiment overlap the downstream ends of the discharge nozzles. Cooling air is supplied to the upstream edge portions of the platforms through holes in flanges on the discharge nozzles. The seal assembly defines a chamber adjacent the platform extensions which is supplied with cooling air through metering holes in the seal assembly which provides part of a boundary for a cooling air chamber, the boundary of the chamber having cooling air holes for metering cooling air into the chamber to cool the upstream portion of the nozzle guide vane outer platforms. Cooling air exits the chamber through holes in the platform extensions to film cool them.
摘要翻译：燃气涡轮发动机中的冷却和密封装置包括在喷嘴导向叶片和燃烧室排出喷嘴之间延伸的密封组件。喷嘴导叶具有具有延伸部的平台，在一个实施例中，该延伸部与排放喷嘴的下游端重叠。冷却空气通过排放喷嘴上的凸缘中的孔被供应到平台的上游边缘部分。密封组件限定了邻近平台延伸部分的室，该冷却空气通过密封组件中的计量孔供应冷却空气，该冷却空气为冷却空气室提供了一部分边界，该室的边界具有冷却空气孔，用于将冷却空气计入以冷却喷嘴导向叶片外平台的上游部分。冷却空气通过平台延伸部分中的孔离开室以使其冷却。

3. 发明授权

US5407319A Sealing structures for gas turbine engines 失效
标题翻译：燃气轮机发动机密封结构
公开(公告)号：US5407319A
公开(公告)日：1995-04-18
申请号：US207626
申请日：1994-03-09
申请人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
发明人： Ian W. R. Harrogate , David H. Taylor , Arthur B. Griffin , David W. Tuson
IPC分类号： F01D9/02 , F01D9/04 , F01D11/00 , F02C7/00 , F02C7/28 , F01D5/18
CPC分类号： F01D9/023 , F01D11/005 , Y02T50/671 , Y02T50/675
摘要： A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly (42,30) extending between nozzle guide vanes (20) and combustion chamber discharge nozzles (22). The nozzle guide vanes (20) have platforms (34,36) having extensions (34A,36A) which in one embodiment overlap the downstream ends of the discharge nozzles (22). Cooling air is supplied to the upstream edge portions of the platforms through holes (26,28C) in flanges (24,28) on the discharge nozzles (22). The seal assembly (42,30) defines a chamber (58,70) adjacent the platform extensions which is supplied with cooling air through metering holes (56,68) in the seal assembly. Cooling air exits the chamber (58,70) through holes (34B,36B) in the platform extensions to film cool them.
摘要翻译：燃气涡轮发动机中的冷却和密封装置包括在喷嘴导向叶片（20）和燃烧室排出喷嘴（22）之间延伸的密封组件（42,30）。喷嘴导向叶片（20）具有在一个实施例中与排放喷嘴（22）的下游端重叠的延伸部（34A，36A）的平台（34,36）。冷却空气通过排放喷嘴（22）上的凸缘（24,28）中的孔（26,28C）供应到平台的上游边缘部分。密封组件（42,30）限定了邻近平台延伸部的腔室（58,70），其通过密封组件中的计量孔（56,68）供应冷却空气。冷却空气通过平台延伸部中的孔（34B，36B）离开室（58,70），以使其冷却。

4. 发明授权

US5398496A Gas turbine engines 失效
标题翻译：燃气涡轮发动机
公开(公告)号：US5398496A
公开(公告)日：1995-03-21
申请号：US207614
申请日：1994-03-09
申请人： David H. Taylor , Arthur B. Griffin , David W. Tuson
发明人： David H. Taylor , Arthur B. Griffin , David W. Tuson
IPC分类号： F01D9/02 , F01D9/04 , F02C7/00 , F02C7/28 , F23R3/60
CPC分类号： F01D9/023 , F23R3/60 , Y02T50/675
摘要： A gas turbine engine component support assembly (30) comprises a pair of ring members (64) and (74) defining a slot in which a cranked flange (28) extending from the inner surfaces of an array of combustion chamber discharge nozzles (22) is located. One part (28B) of the cranked flange has projections (28C) which engage with radial slots (76) formed in one of the ring members (74) to provide cross-key location of the discharge nozzles. The support assembly (30) is located adjacent the radially inner platform of an array of nozzle guide vanes (20), and also provides support and location for the vanes.
摘要翻译：一种燃气涡轮发动机部件支撑组件（30）包括一对限定一个狭槽的环形部件（64）和（74），其中从燃烧室排放喷嘴（22）阵列的内表面延伸的曲柄凸缘（28）位于。曲柄法兰的一部分（28B）具有与形成在一个环形构件（74）中的径向槽（76）接合的突起（28C），以提供排出喷嘴的交叉键位置。支撑组件（30）位于喷嘴导向叶片（20）阵列的径向内部平台附近，并且还为叶片提供支撑和定位。

5. 发明授权

US4463568A Fuel injector for gas turbine engines 失效
标题翻译：燃气轮机的燃油喷射器
公开(公告)号：US4463568A
公开(公告)日：1984-08-07
申请号：US400224
申请日：1982-07-20
申请人： Jeffrey D. Willis , Arthur B. Griffin , Bernard W. Boyce
发明人： Jeffrey D. Willis , Arthur B. Griffin , Bernard W. Boyce
IPC分类号： F02C7/232 , F23D17/00 , F23R3/28 , F23R3/36 , F23R3/52 , F02C7/22
CPC分类号： F23D17/002 , F23R3/36 , F24F2011/0073 , Y02E20/344
摘要： A dual fuel injector for a gas turbine engine is arranged to maintain pre-determined air fuel ratios in adjacent upstream and downstream opposite handed vortices and to reduce the deposition of carbon on the injector. The injector comprises a central duct, a deflecting member, a first radially directed outlet, and a shroud which defines an annular duct, and a second radially directed outlet. The ducts receive a supply of compressed air and the central duct receives gaseous fuel from an annular nozzle and the annular duct receives liquid fuel from a set of nozzles.When the injector is operating on liquid fuel, the fuel and air mixture issues from the second outlet and compressed air flows from the first outlet and prevents migration of fuel between the two vortices, thereby maintaining a rich air fuel ratio in the upstream vortex which reduces the emissions of NOx. Also, the flow of air from the first outlet reduces the deposition of carbon from the liquid fuels on the deflecting member.
摘要翻译：用于燃气涡轮发动机的双燃料喷射器被布置成在相邻的上游和下游相对手旋涡中保持预定的空气燃料比并且减少喷射器上的碳沉积。注射器包括中心管道，偏转构件，第一径向指示的出口和限定环形管道的护罩和第二径向指示的出口。管道接收供应的压缩空气，并且中央管道从环形喷嘴接收气体燃料，并且环形管道从一组喷嘴接收液体燃料。当喷射器在液体燃料上运行时，燃料和空气混合物从第二出口发出，压缩空气从第一出口流出并阻止燃料在两个涡流之间的迁移，从而保持上游涡流中的浓空气燃料比， NOx的排放。此外，来自第一出口的空气流减少了来自液体燃料的碳在偏转构件上的沉积。

6. 发明授权

US5134855A Air flow diffuser with path splitter to control fluid flow 失效
标题翻译：具有路径分流器的空气流量扩散器来控制流体流动
公开(公告)号：US5134855A
公开(公告)日：1992-08-04
申请号：US610753
申请日：1990-11-08
申请人： Bryan L. Belcher , Arthur B. Griffin
发明人： Bryan L. Belcher , Arthur B. Griffin
IPC分类号： F02C3/06 , F01D9/04 , F02C3/14 , F02C7/00 , F04D29/54 , F23R3/04 , F23R3/42
CPC分类号： F23R3/04 , F01D9/04 , F04D29/541 , F23R3/42
摘要： A diffuser for use in a gas turbine engine comprises an inner and an outer annular wall which define a divergent flow passage. The divergent flow passage is divided by a splitter to form two annular flow ducts, of different flow area. Introduction of the splitter into the diffuser to form the two annular flow ducts enables the length of the outer annular wall of the diffuser to be reduced. Reducing the length of the outer annular wall of the diffuser increases the flow area between the diffuser and combustion chamber. Air downstream of the diffuser is therefore unrestricted and moves radially outward to the ports in the head of the combustion chamber with minimum pressure loss.

7. 发明授权

US5058374A Injector 失效
标题翻译：注射器
公开(公告)号：US5058374A
公开(公告)日：1991-10-22
申请号：US507483
申请日：1990-04-11
申请人： Bryan L. Bechlher , Arthur B. Griffin
发明人： Bryan L. Bechlher , Arthur B. Griffin
IPC分类号： F02C3/30 , F23L7/00 , F23R3/12
CPC分类号： F23L7/005 , F02C3/305 , F23R3/12
摘要： An injector which is suitable for the injection of fuel and steam into the combustion apparatus of a gas turbine engine. The injector defines a substantially circular cross-section chamber having upstream and downstream ends through which steam operationally flows. Steam is supplied to the upstream end of the chamber in such a manner that it is urged into a vortex as it passes through the chamber. The downstream end of the chamber is outwardly flared so that the steam flow is exhausted from the injector in a genenrally conical configuration.
摘要翻译：一种适于将燃料和蒸汽注入燃气涡轮发动机的燃烧装置的喷射器。喷射器限定具有上游和下游端部的基本上圆形的横截面室，蒸汽通过该端口和下游端流动。蒸汽以这样的方式供应到室的上游端，使得当其通过室时，将其推入涡流。室的下游端向外张开，使得蒸汽流以基本圆锥形构型从喷射器排出。

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