公开(公告)号：US5927066A

公开(公告)日：1999-07-27

申请号：US981154

申请日：1992-11-24

Applicant: Jack R. Shekleton ,  Colin Rodgers

Inventor： Jack R. Shekleton ,  Colin Rodgers

IPC: F23R3/04

CPC classification number: F23R3/04 ,  F05B2220/50 ,  Y02T50/675

Abstract: In a gas turbine engine having gaseous oxidant delivered to a turbine from a source such as a pressurized bottle via a conduit or duct, a compact annular combustor is provided which offers enhanced performance through incorporation of means for uniformly distributing portions of the oxidant utilized as a diluent, and for convective cooling of engine components.

Abstract translation: 在具有经由管道或管道从诸如加压瓶的源递送到涡轮机的气体氧化剂的燃气涡轮发动机中，提供了紧凑的环形燃烧器，其通过并入用于均匀分配用作为 稀释剂，以及用于发动机部件的对流冷却。

公开(公告)号：USRE34962E

公开(公告)日：1995-06-13

申请号：US890916

申请日：1992-05-29

Applicant: Jack R. Shekleton ,  Colin Rodgers ,  John P. Archibald ,  Robert W. Smith

Inventor： Jack R. Shekleton ,  Colin Rodgers ,  John P. Archibald ,  Robert W. Smith

IPC: F02C3/08 ,  F02C7/18 ,  F23R3/04 ,  F23R3/28 ,  F23R3/52

CPC classification number: F23R3/28 ,  F23R3/04 ,  F05B2220/50 ,  F05B2250/322

Abstract: The combustion dynamics and efficiency of gas turbine having an annular combustor 26 provided with fuel injection nozzles 50 that inject fuel generally tangentially is improved by providing the walls 32, 34, 39 of the combustion 26 with cooling air film injectors 70, 86; 72, 88; 74, 90 at substantially equally angularly spaced locations about each such wall and which are oriented to generally tangentially inject a film-like air stream on the associated wall 32, 34, 39.

公开(公告)号：US5343690A

公开(公告)日：1994-09-06

申请号：US33170

申请日：1993-03-16

Applicant: Jack R. Shekleton ,  Colin Rodgers

Inventor： Jack R. Shekleton ,  Colin Rodgers

IPC: F01D5/28 ,  F02C3/05 ,  F02C7/272 ,  F02C7/26

CPC classification number: F02C3/05 ,  F01D5/284 ,  F02C7/272

Abstract: Difficulties in starting a turbine engine, particularly ones having a small volume combustor (83) with a low dome height, may be avoided by a method including the steps of a) forming the turbine engine compressor (48) of a low density, high temperature resistant ceramic material, b) directing pyrotechnic gases at a temperature of at least about 3,000.degree. F. against the blades (48) of the compressor, c) continuing the step of directing until the turbine rotor (44) is rotating at at least about 60 percent of rated speed and d) combusting fuel in the combustor (83) of the turbine engine to maintain the rotor (44) rotating at at least about 60 percent of rated speed.

Abstract translation: 通过包括以下步骤的方法可以避免启动涡轮发动机，特别是具有低拱顶高度的小体积燃烧器（83）的涡轮发动机的困难：a）形成低密度，高温的涡轮发动机压缩机（48） b）将至少约3,000°F的温度的烟火引导到压缩机的叶片（48）上，c）继续引导步骤，直到涡轮转子（44）至少旋转约 60％的额定转速，以及d）燃烧在涡轮发动机的燃烧器（83）中的燃料以保持转子（44）至少旋转至额定速度的约60％。

公开(公告)号：US5261224A

公开(公告)日：1993-11-16

申请号：US970101

申请日：1992-11-02

Applicant: Jack R. Shekleton ,  Steven A. Sachrison

Inventor： Jack R. Shekleton ,  Steven A. Sachrison

IPC: F23R3/00 ,  F23R3/04 ,  F23R3/28 ,  F23R3/34

CPC classification number: F23R3/002 ,  F23R3/045 ,  F23R3/28 ,  F23R3/346

Abstract: Difficulties in achieving reliable starts in gas turbine engines operating at high altitude are avoided in a gas turbine engine including a rotary compressor (10), a rotary turbine wheel (12) coupled to the compressor (10) to drive the same, and a nozzle (42) for directing gases of combustion against the turbine wheel (12). An annular combustor (34) has an outlet (40) connected to the nozzle (42) and an opposed dome (38) that is axially spaced from the outlet (40). At least three sets of air injection openings (80, 92, 100) are axially spaced from one another with one set (82) in close proximity to the dome (38). Fuel injectors (86, 94) are associated with two of the sets (80, 92, 100), including the one set (80) and another of the sets (92) that is nearest the one set (80). The air injection openings of the sets (80 and 92) and the fuel injectors (86, 94) are constructed, arranged and sized so that the air/fuel ratio of air injected by each of the sets (80, 92) is no more than about 5/1 and the remaining set of air injection openings (100) is constructed, arranged and sized so that the total air/fuel ratio of air and fuel through all of the sets (80, 92, 100) and fuel injectors (86, 94) is approximately stoichiometric.

Abstract translation: 在包括旋转式压缩机（10），联接到压缩机（10）的旋转涡轮机叶轮（12）以驱动旋转式压缩机（10）的燃气涡轮发动机中，避免了在高空作业的燃气涡轮发动机中实现可靠启动的困难，以及喷嘴 （42），用于将燃烧气体引导到涡轮机叶轮（12）。 环形燃烧器（34）具有连接到喷嘴（42）的出口（40）和与出口（40）轴向间隔开的相对的圆顶（38）。 至少三组空气喷射开口（80,92,100）彼此轴向间隔开，一组（82）紧邻穹顶（38）。 燃料喷射器（86,94）与两组（80,92,100）中的两个相关联，包括一组（80）和最靠近一组（80）的组（92）中的另一组。 组（80和92）和燃料喷射器（86,94）的空气喷射开口被构造，布置和定尺寸使得由每个组（80,92）喷射的空气的空气/燃料比不再多 大约5/1，剩余的一组空气喷射开口（100）被构造，布置和定尺寸，使得空气和燃料通过所有组（80,92,100）和燃料喷射器（ 86，94）是大致化学计量的。

公开(公告)号：US5163287A

公开(公告)日：1992-11-17

申请号：US455244

申请日：1989-12-22

Applicant: Jack R. Shekleton ,  Robert W. Smith

Inventor： Jack R. Shekleton ,  Robert W. Smith

IPC: F02C7/264 ,  F23R3/14 ,  F23R3/28

CPC classification number: F23R3/28 ,  F02C7/264 ,  F23R3/14

Abstract: In order to optimize ignition capabilities, while at the same time enhancing the life span of an igniter, a stored energy combustor (10) has an igniter (34) disposed within a fuel injector (26). The fuel injector (26) is disposed in a tubular extension (16) leading to a combustion chamber (20) and has a discharge end (28) communicating with a point of entry into the combustion chamber (20). An oxidant inlet port (24) is provided upstream of the combustion chamber (20) for directing oxidant into the combustion chamber (20). The oxidant inlet port (24) directs oxidant through the tubular extension (16) leading to the combustion chamber (20) in surrounding relation to the fuel injector (26). With this arrangement, the igniter (34) is disposed within the fuel injector (26) along a longitudinal axis (22) of the stored energy combustor (10).

Abstract translation: 为了优化点火能力，在同时增加点火器的寿命的同时，储能燃烧器（10）具有设置在燃料喷射器（26）内的点火器（34）。 燃料喷射器（26）设置在通向燃烧室（20）的管状延伸部（16）中并且具有与进入燃烧室（20）的入口连通的排出端（28）。 氧化剂入口（24）设置在燃烧室（20）的上游，用于将氧化剂引导到燃烧室（20）中。 氧化剂入口（24）引导氧化剂通过与燃料喷射器（26）相关的通向燃烧室（20）的管状延伸部（16）。 利用这种布置，点火器（34）沿着存储的能量燃烧器（10）的纵向轴线（22）设置在燃料喷射器（26）内。

公开(公告)号：US5136838A

公开(公告)日：1992-08-11

申请号：US447444

申请日：1989-12-07

Applicant: Jack R. Shekleton ,  Robert W. Smith

Inventor： Jack R. Shekleton ,  Robert W. Smith

IPC: B64D41/00 ,  F02C7/277 ,  F02C7/32

CPC classification number: F02C7/32 ,  B64D41/00 ,  F02C7/277 ,  F05D2220/50

Abstract: Difficulties with starting reliability and/or combustion stability in hot gas generating systems are avoided in a construction including a storage vessel (36) for storing an oxidant; a fuel supply (22) and a combustion chamber (26) having an outlet (30) for hot gas. A fuel injection nozzle (28) provides fuel from the supply (22) to the combustion chamber (26) while an oxidant duct (44) connects the vessel (36) to the combustion chamber (26). A choked orifice (46) is disposed in the duct (44) just upstream of the combustion chamber (26) and a bypass duct (50) interconnects the combustion chamber outlet (30) and the oxidant duct (44) between the choked orifice (46) and the combustion chamber (26). A selectively operable valve (53) is disposed in the bypass duct (50) and a pressure regulator (42) is disposed in the oxidant duct (44) for selectively controlling the pressure of oxidant applied to the choked orifice (46).

Abstract translation: 在包括用于储存氧化剂的储存容器（36）的结构中，避免了在热气体发生系统中启动可靠性和/或燃烧稳定性的困难; 燃料供应装置（22）和具有用于热气体的出口（30）的燃烧室（26）。 燃料喷射喷嘴（28）将燃料从供应源（22）提供给燃烧室（26），而氧化剂管道（44）将容器（36）连接到燃烧室（26）。 扼流孔（46）刚刚在燃烧室（26）的上游设置在管道（44）中，并且旁路管道（50）将燃烧室出口（30）和氧化剂管道（44） 46）和燃烧室（26）。 选择性操作的阀（53）设置在旁路管道（50）中，并且压力调节器（42）设置在氧化剂管道（44）中，用于选择性地控制施加到扼流孔（46）的氧化剂的压力。

公开(公告)号：US5119636A

公开(公告)日：1992-06-09

申请号：US455509

申请日：1989-12-21

Applicant: Anthony Batakis ,  Jack R. Shekleton

Inventor： Anthony Batakis ,  Jack R. Shekleton

IPC: F02C7/22 ,  F23R3/28

CPC classification number: F23R3/283 ,  F02C7/22

Abstract: Manifold head effects at low fuel flows in a fuel injected air breathing turbine are minimized by utilizing fuel injectors having fuel injecting tubes (66) with open ends (70) for fuel injection and provided with elongated capillary tubes (88) upstream thereof and connected to receive fuel from a fuel manifold (48) having an inlet (56) while uniform, relatively low velocity fuel exit flow from the ends (70) the injecting tubes (66) is achieved through the use of internal impingement surfaces (96, 102, 106, 110, 124). Pressure loss differences contributing to nonuniform fuel flow and resulting from some fuel injecting tubes (66) be more distant from the manifold inlet (56) are minimized by shortening the length of the capillary tubes (88) furthest from the manifold inlet (56).

Abstract translation: 通过使用具有燃料喷射管（66）的燃料喷射器（66），燃料喷射空气呼吸涡轮中的低燃料流动的歧管头部效应被最小化，燃料喷射管具有用于燃料喷射的开口端（70），并在其上游设置有细长的毛细管（88）并连接到 从具有入口（56）的燃料歧管（48）接收燃料，同时通过使用内部冲击表面（96,102，...）实现来自端部（70）的均匀，相对低速的燃料出口流动， 106，110，124）。 通过缩短最远离歧管入口（56）的毛细管（88）的长度，导致不均匀燃料流动引起的压力损失差异和由歧管入口（56）更远的一些燃料喷射管（66）产生的压力损失差异最小化。

公开(公告)号：US5115637A

公开(公告)日：1992-05-26

申请号：US455270

申请日：1989-12-22

Applicant: Jack R. Shekleton

Inventor： Jack R. Shekleton

IPC: F02C7/26

CPC classification number: F02C7/26

Abstract: In order to assist in starting a gas turbine engine (10), hot pressurized exhaust gases are supplied through relatively large hot gas supply tubes (22) for direct impingement on turbine blades (14) to drive a turbine rotor (12). The relatively large hot gas supply tubes (22) are located in immediate proximity to a flame zone (32) of a combustor (16). This proximate location of the relatively large hot gas supply tubes (22) facilitates diversion of a small amount of hot pressurized, exhaust gases to the flame zone (32) through a flow control orifice (28) for the purpose of initiating ignition in the combustor (16) wherein the BTU energy of the exhaust gases is transferred to the combustor (16) during the starting thereof. The relatively large hot gas supply tubes (22) ensure a high mass flow rate of hot pressurized exhaust gases with some being directed to the flame zone (32) in a manner minimizing heat loss which enhances ignition reliability. Through the utilization of the present invention electrically activated ignitors may be eliminated.

Abstract translation: 为了帮助启动燃气涡轮发动机（10），通过相对较大的热气供应管（22）来供应热加压废气，用于直接冲击在涡轮叶片（14）上以驱动涡轮转子（12）。 相对较大的热气体供应管（22）位于紧邻燃烧器（16）的火焰区域（32）处。 相对较大的热气体供应管（22）的该邻近位置有助于通过流量控制孔（28）将少量的热加压废气引导到火焰区域（32），以便在燃烧器中引发点火 （16），其中废气的BTU能量在其起动期间被传递到燃烧器（16）。 相对较大的热气供应管（22）确保热加压废气的高质量流率，其中一些以一定的方式被引导到火焰区（32），以最大限度地减少热损失，这提高了点火可靠性。 通过利用本发明，可以消除电激活的点火器。

公开(公告)号：US5113648A

公开(公告)日：1992-05-19

申请号：US486132

申请日：1990-02-28

Applicant: Jack R. Shekleton ,  Ray C. Ramirez

Inventor： Jack R. Shekleton ,  Ray C. Ramirez

IPC: F23R3/06

CPC classification number: F23R3/06 ,  F05B2260/63

Abstract: In order to avoid plugging the air passageways (42a) of fuel injectors (42) with carbon particles or lumps in a gas turbine engine (10), the gas turbine engine (10) includes an annular combustor (18) having radial dilution air injection. The gas turbine engine (10) also includes a rotor (12) having turbine blades (14) and a nozzle (16) adjacent the turbine blades (14) which is adapted to direct hot gases of combustion at the turbine blades (14) to cause rotation of the rotor (12). The annular combustor (18) is disposed about the rotor (12) and has an outlet (20) to the nozzle (16), spaced inner and outer walls (22 and 24), and a generally radially extending wall (26) connecting the inner and outer walls (22 and 24). The gas turbine engine (10) further includes a housing (28) substantially surrounding the annular combustor (18) in spaced relation to the inner, outer, and radially extending walls (22, 24 and 26) to define a dilution air flow path (30). The annular combustor (18) has a combustion annulus (36) defined by the inner, outer, and radially extending walls (22, 24 and 26), and a plurality of radially disposed air blast fuel injectors (42). The gas turbine engine (10) also includes dilution air holes (48) for bleeding air into the combustion annulus (36) to mix with the hot gases of combustion. With this arrangement, the gas turbine engine includes a screen or wire mesh for preventing matter potentially obstructive to an air passageway of a fuel injector from passing from a dilution air hole into the air passageway.

Abstract translation: 为了避免燃料喷射器（42）的空气通道（42a）与燃气涡轮发动机（10）中的碳颗粒或块块堵塞，燃气涡轮发动机（10）包括具有径向稀释空气喷射的环形燃烧器（18） 。 燃气涡轮发动机（10）还包括具有涡轮叶片（14）的转子（12）和与涡轮机叶片（14）相邻的喷嘴（16），该喷嘴适于将涡轮机叶片（14）处的燃烧热气体引导至 引起转子（12）的旋转。 环形燃烧器（18）围绕转子（12）设置并且具有到喷嘴（16）的出口（20），间隔开的内壁和外壁（22和24）以及大致径向延伸的壁（26） 内壁和外壁（22和24）。 燃气涡轮发动机（10）还包括基本上围绕环形燃烧器（18）围绕内部，外部和径向延伸的壁（22,24和26）间隔开的壳体（28），以限定稀释气流路径 30）。 环形燃烧器（18）具有由内部，外部和径向延伸的壁（22,24和26）限定的燃烧环（36）和多个径向设置的鼓风燃料喷射器（42）。 燃气涡轮发动机（10）还包括用于将空气排放到燃烧环（36）中以与热的燃烧气体混合的稀释气孔（48）。 利用这种布置，燃气涡轮发动机包括用于防止潜在地阻碍燃料喷射器的空气通道的物质从稀释空气孔进入空气通道的筛网或丝网。

公开(公告)号：US5111655A

公开(公告)日：1992-05-12

申请号：US455245

申请日：1989-12-22

Applicant: Jack R. Shekleton

Inventor： Jack R. Shekleton

IPC: F23R3/12 ,  F23R3/28 ,  F23R3/52

CPC classification number: F23R3/12 ,  F23R3/28 ,  F23R3/52 ,  F05B2220/50 ,  Y02T50/675

Abstract: In order to reduce weight while also minimizing volume and pressure drop in a combustor assembly (18) for a turbine engine, the combustor assembly (18) includes an annular combustion chamber having a combustion space (20) defined entirely be an annular combustor case (22). The combustion chamber (18) is adapted to combust fuel and air in the combustion space (20) to generate gases of combustion. It has a combustor outlet (26) leading to a turbine nozzle (16). The outlet (26) is defined by a pair of turbine shrouds (28, 30). It also has a combustor inlet (32) leading to the combustion space (20). The combustor inlet (32) is defined by the combustor case (22) and one of the turbine shrouds (28). The combustion chamber (18) is adapted to receive injected air at the combustor inlet (32) in a manner creating a generally annular air flow in the combustion chamber (18) about the combustor case (22). In addition, the combustor assembly (18 ) is such that fuel in injected from a source into the combustion chamber (18) in the form of a fuel film (38) at the combustor inlet (32) radially inwardly of and directed parallel to the injected air which is preferably swirled to assist in atomizing the fuel film (38).

Abstract translation: 为了减轻重量，同时还使用于涡轮发动机的燃烧器组件（18）中的体积和压降最小化，燃烧器组件（18）包括环形燃烧室，其具有完全限定为环形燃烧器壳体的燃烧空间（20） 22）。 燃烧室（18）适于燃烧燃烧空间（20）中的燃料和空气以产生燃烧气体。 它具有通向涡轮喷嘴（16）的燃烧器出口（26）。 出口（26）由一对涡轮机罩（28,30）限定。 它还具有通向燃烧空间（20）的燃烧器入口（32）。 燃烧器入口（32）由燃烧器壳体（22）和涡轮机罩（28）中的一个限定。 燃烧室（18）适于在燃烧器入口（32）处以在燃烧器壳体（22）周围的燃烧室（18）中形成大致环形空气流的方式接纳喷射空气。 另外，燃烧器组件（18）使得在燃烧器入口（32）处以燃料膜（38）的形式从燃料源（18）喷射到燃烧室（18）中的燃料在径向向内并平行于燃烧室 喷射的空气优选旋转以帮助雾化燃料膜（38）。