公开(公告)号：WO2013101805A1

公开(公告)日：2013-07-04

申请号：PCT/US2012/071614

申请日：2012-12-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： HASEL, Karl L. ,  STAUBACH, Joseph B. ,  MERRY, Brian D. ,  SUCIU, Gabriel L. ,  DYE, Christohper M.

IPC: F01D1/04

CPC classification number: F02C3/107 ,  F02K3/06

Abstract: A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.

Abstract translation: 燃气涡轮发动机包括风扇部分，被配置为驱动风扇部分的齿轮装置，压缩机部分和涡轮部分。 压缩机部分包括低压压缩机部分和高压压缩机部分。 涡轮部分构造成驱动压缩机部分和齿轮装置。 由所述低压压缩机部分的压力比与所述高压压缩机部分的压力比的组合提供的总体压力比大于约35.低压压缩机部分的压力比介于约 而高压压缩机部分的压力比为约7至约15。

公开(公告)号：WO2014109811A3

公开(公告)日：2014-07-17

申请号：PCT/US2013/066531

申请日：2013-10-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  CHANDLER, Jesse M. ,  STAUBACH, Joseph B. ,  SUYDAM, Adam Joseph

IPC: F02K3/062 ,  F02C7/36 ,  F02C7/32 ,  B64D27/14 ,  B64D29/04 ,  B64D33/04

Abstract: A gas turbine engine has a core engine incorporating a turbine, and a manifold positioned downstream of the turbine. The manifold delivers gas downstream of the turbine into at least two nacelles, with each of the nacelles receiving a fan rotor. The fan rotor is fixed to rotate with a tip turbine mounted at a radially outer location of the fan rotor, with the tip turbine being in the path of gases from the manifold. An aircraft is also disclosed.

Abstract translation: 燃气涡轮发动机具有包含涡轮的核心发动机和位于涡轮下游的歧管。 歧管将涡轮下游的气体输送到至少两个机舱中，每个机舱接收风扇转子。 风扇转子被固定以随着安装在风扇转子的径向外部位置处的尖端涡轮机旋转，其中尖端涡轮机处于来自歧管的气体的路径中。 还披露了一架飞机。

公开(公告)号：WO2013119535A1

公开(公告)日：2013-08-15

申请号：PCT/US2013/024720

申请日：2013-02-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： SUCIU, Gabriel L. ,  DYE, Christopher ,  STAUBACH, Joseph B.

IPC: F02K3/06 ,  F02K3/02 ,  F02K5/00 ,  F02C7/00

CPC classification number: F02K3/06 ,  F02C3/107 ,  F02C7/04 ,  F02C7/36 ,  F05D2210/40 ,  F05D2250/313 ,  F05D2250/314 ,  Y10T29/4932 ,  Y10T29/49323

Abstract: A separate propulsion unit incorporating a free turbine and a fan receives gases from a plurality of core engines. The core engines each include a compressor, a turbine and a combustion section. The core engines in combination pass gases across the free turbine. A method is also disclosed.

Abstract translation: 结合有自由涡轮机和风扇的单独的推进单元接收来自多个核心发动机的气体。 核心发动机各自包括压缩机，涡轮机和燃烧部分。 核心发动机组合通过自由涡轮机的气体。 还公开了一种方法。

公开(公告)号：EP3683424A1

公开(公告)日：2020-07-22

申请号：EP20152218.2

申请日：2020-01-16

Applicant: United Technologies Corporation

Inventor： SOMANATH, Nagendra ,  McAULIFFE, Brendan T. ,  STAUBACH, Joseph B.

IPC: F02C6/18 ,  F01K23/10 ,  F01K25/10 ,  F02C7/18

Abstract: A gas turbine engine (100) includes a primary flowpath fluidly connecting a compressor section (110), a combustor section (120), and a turbine section (130). A heat exchanger (150) is disposed in the primary flowpath downstream of the turbine section (130). The heat exchanger (150) includes a first inlet for receiving fluid from the primary flowpath and a first outlet for expelling fluid received at the first inlet. The heat exchanger (150) further includes a second inlet fluidly connected to a supercritical CO2 (sCO2) bottoming cycle (160) and a second outlet connected to the sCO2 bottoming cycle (160). The sCO2 bottoming cycle (160) is a recuperated Brayton cycle (160).

公开(公告)号：EP3318743A1

公开(公告)日：2018-05-09

申请号：EP17200638.9

申请日：2017-11-08

Applicant: United Technologies Corporation

Inventor： STAUBACH, Joseph B. ,  SNAPE, Nathan

IPC: F02K3/115 ,  F02C6/08 ,  F02C7/141 ,  B64D13/06

Abstract: An intercooled cooling system (100) for a gas turbine engine (20) includes cooling stages (110,115) in fluid communication with an air stream (275) utilized for cooling. A first cooling stage (110) is fluidly coupled to a bleed port (145,165) of the gas turbine engine (20) to receive and cool bleed air with the air stream (275) to produce a cool bleed air. The intercooled cooling system (100) includes a pump (105) fluidly coupled to the first cooling stage (110) to receive and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage (115) is fluidly coupled to the pump (105) to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. The intercooled cooling system includes an air cycle machine (190) in fluid communication to outputs of the cooling stages (110,115) to selectively receive the cool bleed air or the intercooled cooling air.

Abstract translation: 用于燃气涡轮发动机（20）的中冷冷却系统（100）包括与用于冷却的空气流（275）流体连通的冷却级（110,115）。 第一冷却阶段（110）流体联接到燃气涡轮发动机（20）的排放端口（145,165）以接收并冷却排气与空气流（275）以产生冷排气。 中冷冷却系统（100）包括流体联接到第一冷却级（110）的泵（105），以接收和增加冷排气的压力以产生加压的冷排气。 第二冷却阶段（115）流体联接到泵（105）以接收和冷却加压的冷排气以产生中冷冷却空气。 中冷冷却系统包括与冷却级（110,115）的输出流体连通的空气循环机（190），以选择性地接收冷排气或中冷冷却空气。

公开(公告)号：EP3115589A1

公开(公告)日：2017-01-11

申请号：EP16178668.6

申请日：2016-07-08

Applicant: United Technologies Corporation

Inventor： ADAMS, Paul R. ,  MAGGE, Shankar S. ,  STAUBACH, Joseph B. ,  LORD, Wesley K. ,  SCHWARZ, Frederick M. ,  SUCIU, Gabriel L.

IPC: F02K3/06 ,  F02C3/107

CPC classification number: F02C3/107 ,  F02K3/06

Abstract: A turbofan engine (20) includes an engine case (22), a gaspath through the engine case (22), a fan (42) having a circumferential array of fan blades, a compressor in fluid communication with the fan (42), a combustor (48) in fluid communication with the compressor, and a turbine in fluid communication with the combustor (48). The turbine has a fan drive turbine section (27) having 3 to 6 blade stages (200, 202, 204). A speed reduction mechanism (46) couples the fan drive turbine section (27) to the fan (42). A bypass area ratio is between 8.0 and 20.0. A ratio of maximum gaspath radius along the fan drive turbine section (27) to maximum radius of the fan (42) is less than 0.50. A ratio of a turbine section airfoil count to the bypass area ratio is between 10 and 170.

Abstract translation: 涡轮风扇发动机（20）包括发动机壳体（22），通过发动机壳体（22）的气路，具有圆周阵列的风扇叶片的风扇（42），与风扇（42）流体连通的压缩机， 与压缩机流体连通的燃烧器（48）和与燃烧器（48）流体连通的涡轮机。 涡轮机具有风扇驱动涡轮部分（27），其具有3至6个叶片级（200,202,204）。 减速机构（46）将风扇驱动涡轮部分（27）连接到风扇（42）。 旁路面积比在8.0和20.0之间。 沿着风扇驱动涡轮部分（27）的最大气路径半径与风扇（42）的最大半径的比值小于0.50。 涡轮机翼型计数与旁路面积比的比值在10和170之间。

公开(公告)号：EP3301265B1

公开(公告)日：2020-10-28

申请号：EP17193812.9

申请日：2017-09-28

Applicant: United Technologies Corporation

Inventor： FORCIER, Mathew P. ,  STAUBACH, Joseph B.

IPC: F01D25/12 ,  F28D15/02 ,  F28F21/02

公开(公告)号：EP3546737A1

公开(公告)日：2019-10-02

申请号：EP19166650.2

申请日：2019-04-01

Applicant: United Technologies Corporation

Inventor： HASEL, Karl L. ,  STAUBACH, Joseph B. ,  MERRY, Brian D. ,  SUCIU, Gabriel L. ,  DYE, Christopher M.

IPC: F02K3/06 ,  F02C7/36 ,  F02C3/107

Abstract: A gas turbine engine (10) includes, among other things, a fan (14; 714), a core engine, a bypass passage (58), and a bypass ratio defined as the volume of air passing into the bypass passage (58) compared to the volume of air passing into the core engine, the bypass ratio being greater than or equal to 10. A gear arrangement (62; 762) drives the fan (14; 714). A compressor section (19) includes both a low pressure compressor (18; 718) and a high pressure compressor (22). A turbine section (21) drives the gear arrangement (62; 762). An overall pressure ratio is provided by the combination of a pressure ratio across the low pressure compressor (18; 718) and a pressure ratio across the high pressure compressor (22), and greater than 50, measured at sea level and at a static, full-rated takeoff power. The pressure ratio across the high pressure compressor (22) is greater than 7.

公开(公告)号：EP3318742A1

公开(公告)日：2018-05-09

申请号：EP17200678.5

申请日：2017-11-08

Applicant: United Technologies Corporation

Inventor： STAUBACH, Joseph B. ,  SNAPE, Nathan

IPC: F02K3/077 ,  F02C7/18

CPC classification number: F02C7/185 ,  F02C3/04 ,  F02C9/18 ,  F02K3/077 ,  F05D2220/32 ,  F05D2260/212 ,  F05D2260/213 ,  Y02T50/675

Abstract: An intercooled cooling system (100;200;300) for a gas turbine engine (20) is provided. The intercooled cooling system includes a plurality of cooling stages (110,115;210,215;310,315) in fluid communication with an air stream utilized for cooling. A first cooling stage (110;210;310) of the plurality of cooling stages is fluidly coupled to a bleed port (145) of a compressor of the gas turbine engine to receive and cool bleed air with the air stream to produce a cool bleed air. The intercooled cooling system also includes a pump (105) fluidly coupled to the first cooling stage (110;210;310) to receive the cool bleed air and increase a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage (115;215;315) of the plurality of cooling stages is fluidly coupled to the pump (105) to receive and cool the pressurized cool bleed air to produce an intercooled cooling air, which is provided to the gas turbine engine (20).

Abstract translation: 提供了用于燃气涡轮发动机（20）的中间冷却系统（100; 200; 300）。 中冷冷却系统包括与用于冷却的空气流体流体连通的多个冷却级（110,115; 210,215; 310,315）。 多个冷却级中的第一冷却级（110; 210; 310）流体联接到燃气涡轮发动机的压缩机的排放端口（145），以接收和冷却排放的空气与空气流，以产生冷排放 空气。 中冷冷却系统还包括与第一冷却级（110; 210; 310）流体连接的泵（105），以接收冷的放气并增加冷放气的压力以产生加压的冷放气。 多个冷却级中的第二冷却级（115; 215; 315）流体联接至泵（105）以接收并冷却加压的冷抽气以产生中冷冷却空气，该冷空气被提供至燃气涡轮发动机 （20）。

公开(公告)号：EP3301265A1

公开(公告)日：2018-04-04

申请号：EP17193812.9

申请日：2017-09-28

Applicant: United Technologies Corporation

Inventor： FORCIER, Mathew P. ,  STAUBACH, Joseph B.

IPC: F01D25/12 ,  F28D15/02 ,  F28F21/02

Abstract: A graphene heat pipe for a gas turbine engine includes a body comprising graphene (104A). The body has a hot side (106A) to accept heat from the gas turbine engine, a cold side (108A) to reject heat from the body, and an adiabatic portion (110A) to flow heat within the body between the hot side and the cold side. A gas turbine engine of an aircraft comprises a fan section, a compressor section, and a graphene heat pipe flowing heat from a compressor flow path to a fan flow path. A method for cooling a compressor flow path of a gas turbine engine includes the use of a graphene heat pipe.

Abstract translation: 用于燃气涡轮发动机的石墨烯热管包括包含石墨烯（104A）的主体。 本体具有用于接收来自燃气涡轮发动机的热量的热侧（106A），用于排出来自本体的热量的冷侧（108A）以及使热量在本体内在热侧和热侧之间流动的绝热部分（110A） 冷的一面。 飞行器的燃气涡轮发动机包括风扇部分，压缩机部分和石墨烯热管，热量从压缩机流动路径流动到风扇流动路径。 用于冷却燃气涡轮发动机的压缩机流动路径的方法包括使用石墨烯热管。