公开(公告)号：US10815889B2

公开(公告)日：2020-10-27

申请号：US16027787

申请日：2018-07-05

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Jorn Axel Glahn

IPC: F02C7/14 ,  F02C3/04 ,  F02C7/18 ,  G07C5/00

Abstract: A gas turbine engine includes a first tap connected to a compressor section to deliver air at a first pressure. A heat exchanger is downstream of the first tap. A cooling air valve selectively blocks flow of cooling air across the heat exchanger. A cooling compressor is downstream of the heat exchanger and pressurizes the air from the first tap to a greater second pressure. A shut off valve selectively stops flow of the air between the heat exchanger and the cooling compressor. A controller controls the cooling air valve, the shut off valve, and the cooling compressor such that the flow of the air is stopped between the heat exchanger and the cooling compressor only after the controller has stopped the cooling compressor. A monitoring system communicates with the controller and includes a pressure sensor and a temperature sensor downstream of the cooling compressor.

公开(公告)号：US10794288B2

公开(公告)日：2020-10-06

申请号：US14793119

申请日：2015-07-07

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F02C7/18 ,  F02K3/06 ,  F02C7/141 ,  F02C9/18 ,  F02K3/075 ,  F02C7/042 ,  F02C7/16 ,  F02C7/04 ,  F02K3/02

Abstract: An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.

公开(公告)号：US10760488B2

公开(公告)日：2020-09-01

申请号：US15013125

申请日：2016-02-02

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C1/00 ,  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 gas turbine engine according to an example of the present disclosure includes, among other things, a fan section having a plurality of fan blades. The plurality of fan blades has a peak tip radius Rt and an inboard leading edge radius Rh at a first inboard boundary of a first flowpath. A core engine includes a first turbine configured to drive a first compressor, and a fan drive turbine configured to drive the fan section. A method of designing a gas turbine engine is also disclosed.

公开(公告)号：US10718233B2

公开(公告)日：2020-07-21

申请号：US16012152

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Glenn Levasseur ,  Brian D. Merry

IPC: F02C7/18 ,  F01D25/12 ,  F04D29/58 ,  F02K3/06

Abstract: A gas turbine engine includes a plurality of rotatable components housed within a main compressor section and a turbine section. A cooling system is connected to tap air from said main compressor section. A first tap is connected to a first heat exchanger. The first heat exchanger is connected to a cooling compressor for raising a pressure of the tapped air downstream of the first heat exchanger. A second heat exchanger is downstream of the cooling compressor, and a connection is downstream of the second heat exchanger for delivering air to a bearing compartment. A connection intermediate the cooling compressor and the second heat exchanger delivers cooling air to at least one of the rotatable components.

公开(公告)号：US10669890B2

公开(公告)日：2020-06-02

申请号：US16404217

申请日：2019-05-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Lisa I. Brilliant

IPC: F01D25/14 ,  F01D5/08 ,  F01D25/26 ,  F02C7/14 ,  F02C7/24 ,  F02C7/36 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D25/24 ,  F02C3/04

Abstract: A gas turbine engine having an engine axis and method of manufacturing the same is disclosed. The gas turbine engine may comprise a fan configured to drive air, a low pressure compressor section having a core flow path and configured to draw in and compress air flowing along the core flow path, a spool configured to drive the fan, and geared architecture configured to adjust the fan speed. The gas turbine engine may also include a housing defining a compartment that encloses the geared architecture. The housing is disposed between the core flow path and the axis, and includes a shielded mid-section that is in thermal communication with the core flow path of the low pressure compressor section. The shielded mid-section includes an outer layer and an insulator adjacent to the outer layer.

公开(公告)号：US20200025145A1

公开(公告)日：2020-01-23

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: F02K3/06 ,  F02C7/36

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：US20200025106A1

公开(公告)日：2020-01-23

申请号：US16395623

申请日：2019-04-26

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C9/18 ,  F02K3/06 ,  F01D5/28 ,  F02C3/10 ,  F02C7/18 ,  F02C7/32 ,  F02C7/36

Abstract: A gas turbine engine comprises a fan rotor having blades with an outer diameter. The outer diameter is greater than or equal to 77 inches (196 centimeters) and less than or equal to 135 inches (343 centimeter). The fan rotor has less than or equal to 26 fan blades, and is driven by a fan drive turbine through a gear reduction. The gear reduction has a gear ratio of greater than 2.6:1. The fan rotor delivers air into a bypass duct as bypass air, and into a duct leading to a compressor rotor as core air. A ratio of bypass air to the core air is greater than or equal to 12:1. An upstream turbine rotor is upstream of the fan drive turbine and drives a compressor rotor. The upstream turbine rotor has at least two stages, and the fan drive turbine rotor has at least three stages. The turbine blades in at least one stage of the fan drive turbine rotor are provided with a performance enhancing feature, which is at least one of the blades being manufactured by a directionally solidified blade material. The blades are provided as single crystal blades, and have a radially outer platform provided with scalloping to reduce the weight of the blades. The blades are provided with cooling air.

公开(公告)号：US20200025069A1

公开(公告)日：2020-01-23

申请号：US16291241

申请日：2019-03-04

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

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

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan having a plurality of fan blades, and a nacelle surrounding the plurality of fan blades, a compressor section including a low pressure compressor and a high pressure compressor, the low pressure compressor including a plurality of stages, and the high pressure compressor including 6 or more stages. A turbine section includes a fan drive turbine that drives the fan section through a gear arrangement, and including a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor, the power ratio defined by the second power input divided by the first power input, and the power ratio is less than or equal to 1.0

公开(公告)号：US20190383167A1

公开(公告)日：2019-12-19

申请号：US16012152

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Glenn Levasseur ,  Brian D. Merry

IPC: F01D25/12 ,  F02C7/18 ,  F04D29/58

Abstract: A gas turbine engine includes a plurality of rotatable components housed within a main compressor section and a turbine section. A cooling system is connected to tap air from said main compressor section. A first tap is connected to a first heat exchanger. The first heat exchanger is connected to a cooling compressor for raising a pressure of the tapped air downstream of the first heat exchanger. A second heat exchanger is downstream of the cooling compressor, and a connection is downstream of the second heat exchanger for delivering air to a bearing compartment. A connection intermediate the cooling compressor and the second heat exchanger delivers cooling air to at least one of the rotatable components.

公开(公告)号：US20190383157A1

公开(公告)日：2019-12-19

申请号：US16012059

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D15/10 ,  F02C7/36 ,  F02K3/06 ,  H02K11/00 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other things, a fan driven by a fan shaft rotatable about an engine axis; a fan drive electric motor providing a supplemental drive input to the fan; a turbine section driving an input shaft; a geared architecture driven by the input shaft of the turbine section and coupled to the fan shaft to provide a main drive input for driving the fan; and a generator including a rotor supported on the input shaft and a stator disposed on a static structure relative to the rotor, wherein the generator communicates electric power to power the fan drive electric motor.