公开(公告)号：US20150132106A1

公开(公告)日：2015-05-14

申请号：US14602625

申请日：2015-01-22

Applicant: United Technologies Corporation

Inventor： Peter G. Smith ,  Stuart S. Ochs ,  Frederick M. Schwarz

IPC: F01D17/16 ,  F02C9/20

CPC classification number: F01D17/162 ,  F02C9/20 ,  F04D29/563 ,  F05D2220/36

Abstract: A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract translation: 涡轮风扇发动机包括相对于风扇机舱可轴向移动的风扇可变区域喷嘴，以改变风扇喷嘴出口区域，并且在发动机运行期间调节风扇旁路气流的压力比。

公开(公告)号：US20150096303A1

公开(公告)日：2015-04-09

申请号：US14573003

申请日：2014-12-17

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu ,  Daniel Bernard Kupratis ,  William K. Ackermann

IPC: F02C3/04 ,  F02C7/36

CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/107 ,  F02K3/04 ,  F02K3/06

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.

公开(公告)号：US20140286754A1

公开(公告)日：2014-09-25

申请号：US13792303

申请日：2013-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Robert E. Malecki

IPC: F02C7/36

CPC classification number: F02C7/36 ,  B64D33/02 ,  B64D2033/0286 ,  F02C3/10 ,  F02C3/107 ,  F02K3/06 ,  F02K3/068 ,  F05D2220/36 ,  Y02T50/672

Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

Abstract translation: 推进系统包括风扇，齿轮，被配置为驱动齿轮的涡轮，从而驱动风扇。 涡轮机具有出口点，并且在出口处限定直径（Dt）。 机舱围绕核心发动机外壳。 风扇被配置为将空气输送到限定在机舱和核心发动机壳体之间的旁路管道中。 在出口点的下游设有核心发动机排气喷嘴。 核心发动机排气喷嘴的下游最点定义在离出口一定距离处。 距离直径之比大于或等于约0.90。

公开(公告)号：US20130192201A1

公开(公告)日：2013-08-01

申请号：US13645626

申请日：2012-10-05

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02K3/075

CPC classification number: F02C7/06 ,  F02K3/06 ,  F05D2260/40311 ,  Y02T50/671

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

公开(公告)号：US11542016B2

公开(公告)日：2023-01-03

申请号：US16360280

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter ,  Charles E. Lents ,  Nathan Snape ,  Alan H. Epstein

IPC: F25B9/14 ,  B64D33/08 ,  B64D13/06 ,  F25J1/00 ,  B64D13/08 ,  F02C7/141 ,  F02C7/16 ,  F02C9/18 ,  F25J3/04 ,  B01D45/08 ,  B01D53/00 ,  B03C1/28 ,  B64D27/12 ,  F01D15/00 ,  F01D25/12 ,  F02C6/08 ,  F02C7/143 ,  F02C7/18 ,  F02K3/06 ,  F17C7/02 ,  F17C7/04 ,  B64D37/32

Abstract: A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

公开(公告)号：US11492973B2

公开(公告)日：2022-11-08

申请号：US16364524

申请日：2019-03-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F28F7/00 ,  F02C7/18 ,  F02K3/115 ,  F02C7/141 ,  F02C7/20 ,  F04D29/58 ,  F28D1/047 ,  F28D7/06 ,  F28F21/08 ,  F28F9/013 ,  F28D21/00 ,  F04D19/02 ,  F28F9/22

Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.

公开(公告)号：US11168574B2

公开(公告)日：2021-11-09

申请号：US16368150

申请日：2019-03-28

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William K. Ackermann

IPC: F01D11/02 ,  F01D11/00 ,  F16J15/44

Abstract: An assembly is provided for rotational equipment. The assembly includes a circumferentially segmented stator and a rotor radially within the stator. The assembly also includes a seal assembly configured for substantially sealing a gap radially between the stator and the rotor. The seal assembly includes a carrier and a non-contact seal seated with the carrier. The carrier includes a plurality of discrete carrier segments circumferentially arranged around the non-contact seal.

公开(公告)号：US11149643B2

公开(公告)日：2021-10-19

申请号：US15369189

申请日：2016-12-05

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Nathan Snape

IPC: F02C7/18 ,  F02K3/06 ,  F02C3/04 ,  F02C7/141 ,  F02K3/115 ,  F02C9/18

Abstract: A gas turbine engine has a fan rotor delivering air into a bypass duct defined between an outer fan case and an outer interior housing. The fan rotor also delivers air into a compressor section, a combustor, a turbine section. A chamber is defined between the outer interior housing and an inner housing. The inner housing contains the compressor section, the combustor and the turbine section. A first conduit taps hot compressed air to be cooled and passes the air to at least one heat exchanger. The air is cooled in the heat exchanger and returned to a return conduit. The return conduit passes the cooled air to at least one of the turbine section and the compressor section. The heat exchanger has a core exhaust plane. The turbine section has at least a first and a downstream second rotor blade row, with the core exhaust plane located downstream of a center plane of the second blade row.

公开(公告)号：US11047257B2

公开(公告)日：2021-06-29

申请号：US15656444

申请日：2017-07-21

Applicant: United Technologies Corporation

Inventor： Subhradeep Chowdhury ,  David M. Bostwick ,  David Gelwan ,  Frederick M. Schwarz

IPC: F01D19/02 ,  B64D27/12 ,  F01D25/34 ,  F02C6/20 ,  F02C7/277 ,  F02C9/00 ,  B64D41/00 ,  B64F1/36 ,  F02C3/04

Abstract: A system is provided for multi-engine coordination of gas turbine engine motoring in an aircraft. The system includes a controller operable to determine a motoring mode as a selection between a single engine dry motoring mode and a multi-engine dry motoring mode based on at least one temperature of a plurality of gas turbine engines and initiate dry motoring based on the motoring mode.

公开(公告)号：US10823085B2

公开(公告)日：2020-11-03

申请号：US15979906

申请日：2018-05-15

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Matthew P. Forcier

IPC: F02C9/18 ,  F01D25/10 ,  F01D5/08 ,  F01D11/24 ,  F01D9/06 ,  F02C3/34 ,  F02C7/12

Abstract: A gas-circulation system for conditioning a disk of an aircraft may comprise a first takeoff port configured to extract a combusted gas and a second takeoff port configured to extract an uncombusted gas. A first valve may comprise an inlet in fluid communication with the first and second takeoff ports and an outlet of the first valve in fluid communication with the disk.