公开(公告)号：WO2014134517A1

公开(公告)日：2014-09-04

申请号：PCT/US2014/019564

申请日：2014-02-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  ACKERMANN, William K.

IPC: F02C7/12 ,  F01D25/12

CPC classification number: F02C7/18 ,  F01D5/02 ,  F01D9/041 ,  F01D9/065 ,  F01D17/105 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C6/08 ,  F02C7/04 ,  F02C7/06 ,  F02C7/14 ,  F04D29/541 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/676

Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, a turbine section, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said turbine section.

Abstract translation: 提供了一种燃气涡轮发动机，其包括压缩机部分，燃烧器部分，扩散器壳体模块，涡轮部分和歧管。 扩散器壳模块包括在从所述压缩机部分到所述燃烧器部分的环形流动路径内的多个支柱，其中所述多个支柱中的至少一个限定了与所述环形流动路径连通的中跨预扩散器入口。 歧管与所述中跨预扩散器入口和所述涡轮部分连通。

公开(公告)号：WO2014007886A2

公开(公告)日：2014-01-09

申请号：PCT/US2013/034045

申请日：2013-03-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  PICKFORD, Simon ,  ACKERMANN, William K. ,  SNAPE, Nathan

CPC classification number: F01D9/065 ,  F01D1/02 ,  F01D5/02 ,  F01D9/02 ,  F01D25/12 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32 ,  F05D2220/30 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/675

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump at least partially within an interior of the nose cone. The pump is selectively rotated by a motor to communicate air to the interior.

Abstract translation: 示例性的涡轮机组件包括涡轮机的鼻锥，以及至少部分地在鼻锥内部的泵。 泵通过电动机选择性地旋转以将空气传送到内部。

公开(公告)号：WO2013154630A1

公开(公告)日：2013-10-17

申请号：PCT/US2013/021628

申请日：2013-01-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： ACKERMANN, William K. ,  MUNSELL, Peter M.

IPC: F02C7/12 ,  F02C6/08 ,  F02C6/04 ,  F02C7/06 ,  F02G3/00

CPC classification number: F02C6/08 ,  F01D11/04 ,  F01D25/125 ,  F01D25/16 ,  F02C7/06 ,  F02C7/185 ,  F02C7/28 ,  F02C9/18 ,  F05D2260/202 ,  F05D2260/213 ,  Y02T50/676

Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.

Abstract translation: 燃气涡轮发动机包括将缓冲冷却空气与至少一个轴承结构和燃气涡轮发动机的至少一个轴连通的缓冲系统。 缓冲系统包括第一排气供应和调节装置，其调节第一排气供应以使第一缓冲器供应空气处于可接受的温度以对至少一个轴承结构加压并冷却至少一个轴。

公开(公告)号：WO2014134523A1

公开(公告)日：2014-09-04

申请号：PCT/US2014/019573

申请日：2014-02-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  ACKERMANN, William K.

IPC: F01D25/30 ,  F02C7/00

CPC classification number: F02C7/18 ,  F01D5/02 ,  F01D9/041 ,  F01D9/065 ,  F01D17/105 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C6/08 ,  F02C7/04 ,  F02C7/06 ,  F02C7/14 ,  F04D29/541 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/676

Abstract: A gas turbine engine that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and a bearing compartment.

Abstract translation: 一种燃气涡轮发动机，其包括压缩机部分，燃烧器部分，扩散器壳体模块和歧管。 扩散器壳模块包括在从所述压缩机部分到所述燃烧器部分的环形流动路径内的多个支柱，其中所述多个支柱中的至少一个限定了与所述环形流动路径连通的中跨预扩散器入口。 歧管与所述中跨预扩散器入口和轴承室连通。

公开(公告)号：WO2014018142A3

公开(公告)日：2014-01-30

申请号：PCT/US2013/037675

申请日：2013-04-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  SCHWARZ, Frederick M. ,  KUPRATIS, Daniel Bernard ,  MERRY, Brian D. ,  ACKERMANN, William K.

IPC: F01D25/16 ,  F02C7/06

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

Abstract translation: 燃气涡轮发动机包括超高速低压涡轮机，使得由低压涡轮机的出口面积所限定的量乘以低压涡轮机转速的平方与相同的参数 因为高压涡轮机的比率在大约0.5和大约1.5之间。 高压涡轮机由定位在第一轴连接到携带与第二涡轮机部分相关联的涡轮机转子的轮毂的点处的轴承支撑。

公开(公告)号：WO2013154649A2

公开(公告)日：2013-10-17

申请号：PCT/US2013/022388

申请日：2013-01-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  ACKERMANN, William K. ,  KUPRATIS, Daniel Bernard ,  SCHWARZ, Frederick M.

IPC: F02K3/02

CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/36 ,  F05D2220/323 ,  F05D2250/44

Abstract: A gas turbine engine includes a very high speed low pressure turbine such that a quantity defined by the exit area of the low pressure turbine multiplied by the square of the low pressure turbine rotational speed compared to the same parameters for the high pressure turbine is at a ratio between about 0.5 and about 1.5.

Abstract translation: 燃气涡轮发动机包括超高速低压涡轮机，使得由低压涡轮机的出口面积所限定的量乘以低压涡轮机转速的平方与相同的参数 因为高压涡轮机的比率在大约0.5和大约1.5之间。

公开(公告)号：WO2014134536A1

公开(公告)日：2014-09-04

申请号：PCT/US2014/019593

申请日：2014-02-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  ACKERMANN, William K.

IPC: F01D25/30 ,  F02C7/00

CPC classification number: F02C7/18 ,  F01D5/02 ,  F01D9/041 ,  F01D9/065 ,  F01D17/105 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C6/08 ,  F02C7/04 ,  F02C7/06 ,  F02C7/14 ,  F04D29/541 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/676

Abstract: A diffuser for a gas turbine engine is provided that includes an outer shroud, an inner shroud, a multiple of struts between said outer shroud and said inner shroud to define an annular flow path, and a mid-span pre-diffuser inlet in communication with said annular flow path.

Abstract translation: 提供了一种用于燃气涡轮发动机的扩散器，其包括外护罩，内护罩，所述外护罩和所述内护罩之间的多个支柱，以限定环形流动路径，以及中跨预扩散器入口，其与 所述环形流动路径。

公开(公告)号：WO2013180762A1

公开(公告)日：2013-12-05

申请号：PCT/US2013/021711

申请日：2013-01-16

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： GLAHN, Jorn A. ,  ACKERMANN, William K. ,  STRIPINIS, Philip S. ,  SCHMITZ, John T. ,  CRAWLEY, JR, Clifton J.

IPC: F01D17/08

CPC classification number: F01D11/001 ,  F01D3/00 ,  F01D11/025 ,  F05D2260/38 ,  F16J15/442

Abstract: In a featured embodiment, a gas turbine engine has a turbine section and an air moving section upstream of the turbine section. A thrust balance chamber is defined within one of the air moving and turbine sections. The thrust balance chamber is defined between a static structure and a rotating component that is part of at least one of the air moving section and the turbine section. The thrust balance ' chamber is sealed by a first non-contact seal at a radially inner location and a second non-contact seal at a radially outer location. In another embodiment according to the previous embodiment, the air moving section includes one of a fan and a compressor.

Abstract translation: 在特征实施例中，燃气涡轮发动机具有在涡轮部分上游的涡轮部分和空气移动部分。 推力平衡室限定在空气移动和涡轮机部分之一内。 推力平衡室限定在静止结构和作为空气移动部分和涡轮部分中的至少一个的一部分的旋转部件。 推力平衡室由径向内部位置处的第一非接触式密封件和径向外部位置处的第二非接触密封件密封。 在根据前述实施例的另一实施例中，空气移动部分包括风扇和压缩机中的一个。

公开(公告)号：WO2013151842A1

公开(公告)日：2013-10-10

申请号：PCT/US2013/034072

申请日：2013-03-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  PICKFORD, Simon ,  ACKERMANN, William K. ,  SNAPE, Nathan

IPC: F02C7/00 ,  F02C7/12 ,  F02K3/00 ,  F02K99/00 ,  F02C9/00

CPC classification number: F01D13/02 ,  F01D15/08 ,  F01D15/12 ,  F02C7/047 ,  F02C7/14 ,  F02C7/32 ,  F02K3/06 ,  F05D2260/213 ,  Y02T50/675

Abstract: An example turbomachine assembly includes, among other things, a nose cone of a turbomachine, and a pump that is selectively driven by a motor or a shaft to communicate air to an interior of the nose cone. The pump shaft is driven by a dedicated geared architecture.

Abstract translation: 示例性的涡轮机组件包括涡轮机的鼻锥体和由马达或轴选择性地驱动以将空气传送到鼻锥体的内部的泵。 泵轴由专用的齿轮架构驱动。

公开(公告)号：WO2014134519A1

公开(公告)日：2014-09-04

申请号：PCT/US2014/019567

申请日：2014-02-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  ACKERMANN, William K.

IPC: F01D25/30 ,  F02C7/00

CPC classification number: F02C7/18 ,  F01D5/02 ,  F01D9/041 ,  F01D9/065 ,  F01D17/105 ,  F01D25/12 ,  F01D25/24 ,  F02C3/04 ,  F02C6/08 ,  F02C7/04 ,  F02C7/06 ,  F02C7/14 ,  F04D29/541 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/676

Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section with a multiple of pre-swirlers, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold is in communication with said mid-span pre-diffuser inlet and said multiple of pre-swirlers.

Abstract translation: 提供了一种燃气涡轮发动机，其包括压缩机部分，具有多个预旋转器的燃烧器部分，扩散器壳体模块和歧管。 扩散器壳体模块包括在从所述压缩机部分到所述燃烧器部分的环形流动路径内的多个支柱，其中所述多个支柱中的至少一个限定了与所述环形流动路径连通的中跨预扩散器入口。 歧管与所述中跨预扩散器入口和所述多个预旋流器连通。