公开(公告)号：US10578018B2

公开(公告)日：2020-03-03

申请号：US15358267

申请日：2016-11-22

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02K3/00 ,  F02C7/06 ,  F02K1/09 ,  F02C7/36 ,  F02C3/107 ,  F02K3/04 ,  F01D5/02 ,  F01D9/06 ,  F01D17/10 ,  F02C3/06 ,  F02C3/10 ,  F04D29/32 ,  F01D5/06 ,  F02C3/04 ,  F02C7/28 ,  F02C9/18 ,  F02K1/06 ,  F02K3/06 ,  F04D29/38 ,  F16H1/28

Abstract: A turbofan engine according to an exemplary aspect of the present disclosure includes, among other things, a fan having a plurality of blades, and a transmission is configured to drive the fan. The fan blades have a peak tip radius RT. The fan blades have an inboard leading edge radius RH at an inboard boundary of the flowpath. A ratio of RH to RT is less than about 0.40.

公开(公告)号：US20200032715A1

公开(公告)日：2020-01-30

申请号：US16436569

申请日：2019-06-10

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02K3/06

Abstract: A turbofan engine includes a geared architecture for driving a fan about an axis. The geared architecture includes a sun gear rotatable about an axis, a plurality of planet gears driven by the sun gear and a ring gear circumscribing the plurality of planet gears. A carrier supports the plurality of planet gears. The geared architecture includes a power transfer parameter (PTP) defined as power transferred through the geared architecture divided by gear volume multiplied by a gear reduction ratio and is between 219 and 328.

公开(公告)号：US10527151B1

公开(公告)日：2020-01-07

申请号：US16122236

申请日：2018-09-05

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F16H57/04

Abstract: A gas turbine engine includes a bypass ratio greater than about ten (10). A fan is supported on a fan shaft and has a plurality of fan blades. There is a gutter with an annular channel. A gear system is connected to the fan shaft. There is a plurality of planetary gears and a ring gear with an aperture that is axially aligned with the annular channel. The ring gear includes a first portion with a first set of opposed angled teeth separated by a trough from a second portion with a second set of opposed angled teeth. A torque frame at least partially supports the gear system. A low pressure turbine has an inlet, an outlet, and a low pressure turbine pressure ratio greater than 5:1 and a low fan pressure ratio of less than 1.45 across the fan blade alone.

公开(公告)号：US20190382123A1

公开(公告)日：2019-12-19

申请号：US16012040

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Zubair Ahmed Baig

IPC: B64D31/06 ,  B64D27/02 ,  B64D27/12 ,  B64D27/24 ,  B64D31/14 ,  H02K7/18 ,  H02K7/20 ,  H02K11/00 ,  F02C6/20 ,  F02C6/14

Abstract: A propulsion system for an aircraft includes at least one gas turbine engine, an electric auxiliary fan driving motor configured to selectively receive electric power input from one or more electric power sources, and at least one auxiliary propulsion fan configured to selectively receive a motive force from either or both of the at least one gas turbine engine and the electric auxiliary fan driving motor. The propulsion system also includes a controller configured to establish a plurality of takeoff thrust settings of the at least one gas turbine engine and the electric auxiliary fan driving motor such that a minimum total aircraft thrust required for takeoff of the aircraft is produced.

公开(公告)号：US10436115B2

公开(公告)日：2019-10-08

申请号：US15242973

申请日：2016-08-22

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F02C7/20 ,  F01D25/12 ,  F02C6/12

Abstract: A gas turbine engine has a core engine with a compressor section and a turbine section. The compressor section includes a low pressure compressor and a high pressure compressor. A cooling air system taps compressed air and passes the compressed air through a heat exchanger. Cooling air passes over the heat exchanger to cool the compressed air, which is returned to the core engine to provide a cooling function. The heat exchanger is mounted through a flexible mount allowing movement between a static structure and the heat exchanger.

公开(公告)号：US20190293346A1

公开(公告)日：2019-09-26

申请号：US16360277

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter

IPC: F25J3/04 ,  F25B9/14 ,  F02C9/18

Abstract: A propulsion system includes an electric fan propulsion motor with a plurality of propulsion motor windings. The propulsion system also includes a means for controlling a flow rate of a working fluid through a cryogenic working fluid flow control assembly to the propulsion motor windings.

公开(公告)号：US10415478B2

公开(公告)日：2019-09-17

申请号：US15332249

申请日：2016-10-24

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  James D. Hill ,  William K. Ackermann

IPC: F02C7/18 ,  F02C3/04 ,  F01D5/08 ,  F02C6/18 ,  F23R3/04 ,  F01D9/02 ,  F02C6/08

Abstract: Air mixing systems for gas turbine engines include a heat exchanger, a first extraction conduit fluidly coupled to an inlet of the heat exchanger, a second extraction conduit fluidly coupled to an outlet of the heat exchanger, an injection conduit fluidly coupled to the second extraction conduit, an onboard injector supply chamber fluidly coupled to the injection conduit, and an onboard injector fluidly coupled to the onboard injector supply chamber.

公开(公告)号：US20190218933A1

公开(公告)日：2019-07-18

申请号：US16362028

申请日：2019-03-22

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Simon Pickford

IPC: F01D25/12 ,  F01D17/10 ,  F01D5/02 ,  F01D15/12 ,  F02K3/115 ,  F02K3/06 ,  F02C7/14

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D15/12 ,  F01D17/105 ,  F02C7/14 ,  F02K3/06 ,  F02K3/115 ,  F05D2220/36 ,  F05D2230/50 ,  F05D2230/60 ,  F05D2260/213 ,  F05D2260/40311 ,  F05D2260/602 ,  Y02T50/676

Abstract: A method of sizing a heat exchanger for a geared architecture gas turbine engine includes sizing a minimum frontal area of at least one heat exchanger located in communication with a fan bypass airflow such that a ratio of waste heat area to horsepower generation characteristic area is between 1.6 to 8.75.

公开(公告)号：US20190186357A1

公开(公告)日：2019-06-20

申请号：US16282891

申请日：2019-02-22

Applicant: United Technologies Corporation

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

IPC: F02C3/113 ,  F02K3/072 ,  F02C9/16 ,  F02K3/06 ,  F02C3/06 ,  F02C7/36

CPC classification number: F02C3/113 ,  F02C3/06 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06 ,  F02K3/072 ,  F05D2200/221 ,  F05D2220/3215 ,  F05D2220/323 ,  F05D2260/40311 ,  F05D2270/20

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including fan blades, an outer housing that surrounds the fan to define a bypass flow path, a compressor section in fluid communication with the fan, the compressor section including a low pressure compressor section and a high pressure compressor section, a turbine section including a fan drive turbine section driving the fan and the low pressure compressor section and a high pressure turbine section driving the high pressure compressor section. A gear reduction including an epicyclic gear train is between the fan drive turbine section and the low pressure compressor section such that the low pressure compressor section and the fan are rotatable at a common speed and such that the fan is rotatable at a lower speed than the fan drive turbine section. The fan drive turbine section has a first exit area at a first exit point and is rotatable at a first speed, the high pressure turbine section has a second exit area at a second exit point and is rotatable at a second speed, which is higher than the first speed. A first performance quantity is defined as a product of the first speed squared and the first area, a second performance quantity is defined as a product of the second speed squared and the second exit area and a performance ratio of the first performance quantity to the second performance quantity is between 0.2 and 0.8.

公开(公告)号：US20190153960A1

公开(公告)日：2019-05-23

申请号：US16186811

申请日：2018-11-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis

IPC: F02C7/36 ,  F02C3/107 ,  F01D1/26 ,  F02K3/06 ,  F01D15/12

CPC classification number: F02C7/36 ,  F01D1/26 ,  F01D15/12 ,  F02C3/107 ,  F02K3/06 ,  F05D2260/40311 ,  F05D2270/051

Abstract: A gas turbine engine turbine has a compressor section including a low pressure compressor and a high pressure compressor, a turbine section including a low pressure turbine and a high pressure turbine, the high pressure turbine rotatable with the high pressure compressor as a high pressure spool in a first direction about an engine longitudinal axis, the low pressure turbine rotatable as a low pressure spool in the first direction about the engine longitudinal axis, a power density of greater than or equal to 4.75 and less than or equal to 5.5 lbf/in3, a fan section including a fan having a plurality of fan blades, the fan connected to the low pressure spool via a geared architecture such that the fan is rotatable about the engine longitudinal axis in a second direction opposed to the first direction, and a bypass ratio greater than 6.