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：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：US20200291858A1

公开(公告)日：2020-09-17

申请号：US16798969

申请日：2020-02-24

Applicant: United Technologies Corporation

Inventor： Vito Guardi ,  Christopher B. Lyons ,  Nathan Snape

IPC: F02C7/18 ,  F01D25/14 ,  F01D5/18 ,  F02C6/08 ,  F01D9/06 ,  F02C3/04 ,  F02C9/18 ,  F23R3/28

Abstract: A turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. Also included in the turbine engine is a mixing chamber. The mixing chamber is located between the compressor section and the combustor section and the mixing chamber is radially outward of a primary fluid flow path connecting the compressor section, the combustor section, and the turbine section.

公开(公告)号：US10753218B2

公开(公告)日：2020-08-25

申请号：US16017110

申请日：2018-06-25

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Simon Pickford ,  William K. Ackermann ,  Nathan Snape

IPC: F01D9/06 ,  F01D1/02 ,  F01D25/12 ,  F01D5/02 ,  F01D9/02 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32

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.

公开(公告)号：US10669940B2

公开(公告)日：2020-06-02

申请号：US15269014

申请日：2016-09-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan Snape

IPC: F02C7/00 ,  F02C7/18 ,  F02C7/32 ,  F02C6/08 ,  F02C7/36 ,  F02C9/18 ,  F02K3/06

Abstract: A gas turbine engine has a compressor section with a downstream most end and a cooling air tap at a location spaced upstream from the downstream most end. The cooling air tap is passed through at least one boost compressor and at least one heat exchanger, and then passed to a turbine section to cool the turbine section. The boost compressor is driven by a driveshaft which is driven by the turbine section. A boost turbine selectively drives the boost compressor.

公开(公告)号：US10563592B2

公开(公告)日：2020-02-18

申请号：US13715202

申请日：2012-12-14

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Brian D. Merry ,  Allan R. Penda ,  Gabriel L. Suciu

IPC: F02C9/18 ,  B64D13/04 ,  B64D13/08 ,  F02C6/08 ,  F02C6/12 ,  F02C7/141 ,  B64D13/06 ,  F01D17/10

Abstract: A disclosed bleed air system utilizes high pressure air from a high pressure compressor to drive the turbo compressor to increase a pressure of bleed air drawn from the low pressure compressor. Air drawn from the low pressure compressor is at a lower temperature and pressure than that encountered from the high pressure compressor. The turbo compressor increases the pressure of airflow and provides that airflow into the main bleed air passage to be communicated to systems utilizing the bleed air.

公开(公告)号：US20190292985A1

公开(公告)日：2019-09-26

申请号：US15928506

申请日：2018-03-22

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Nathan Snape

IPC: F02C7/18

Abstract: A gas turbine engine includes a plurality of rotating components housed within a main compressor section and a turbine section. A first tap is connected to the main compressor section and configured to deliver air at a first pressure. A heat exchanger is connected downstream of the first tap. A cooling air valve is configured to selectively block flow of cooling air across the heat exchanger. A cooling compressor is connected downstream of the heat exchanger. A shut off valve stops flow between the heat exchanger and the cooling compressor. A second tap is configured to deliver air at a second pressure which is higher than the first pressure. A mixing chamber is connected downstream of the cooling compressor and the second tap. The mixing chamber is configured to deliver air to at least one of the plurality of rotating components. A system stops flow between the cooling compressor and the plurality of rotating components. A controller is configured to modulate flow between the heat exchanger and the plurality of rotating components under certain power conditions of the gas turbine engine. The controller is programmed to control the cooling air valve, the shut off valve and the system such that flow is stopped between the heat exchanger and the cooling compressor only after the cooling compressor has been stopped.

公开(公告)号：US20180195413A1

公开(公告)日：2018-07-12

申请号：US15914519

申请日：2018-03-07

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Simon Pickford

IPC: F01D25/18 ,  F02C7/32 ,  F02C7/14 ,  F02C7/06 ,  F01D25/12 ,  B64D29/08

CPC classification number: F01D25/18 ,  B64D29/08 ,  B64D33/00 ,  F01D25/12 ,  F01M5/002 ,  F02C7/06 ,  F02C7/14 ,  F02C7/32 ,  F05D2260/2214 ,  F16N19/00 ,  Y02T50/675 ,  Y02T50/676

Abstract: A gas turbine engine includes a fan case radially outwardly of a core compartment. A compressor section is located within an engine core compartment and includes a front mount flange and an aft mount flange. An oil tank is mounted to at least one of the fan case or the front and aft mount flanges. The oil tank has a cooling structure integrated into an outer surface such that the oil tank is subjected to cooling air flow from a plurality of air sources.

公开(公告)号：US09988986B2

公开(公告)日：2018-06-05

申请号：US14600445

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  William Ackermann

IPC: F02C7/12

CPC classification number: F02C7/12 ,  F05D2260/213

Abstract: The present disclosure provides systems and methods related to thermal management systems for gas turbine engines. For example, a thermal management system comprises a thermally neutral heat transfer fluid circuit, a first heat exchanger disposed on the fluid circuit, and a second heat exchanger disposed on the fluid circuit.

公开(公告)号：US20180080688A1

公开(公告)日：2018-03-22

申请号：US15269217

申请日：2016-09-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan Snape ,  Joseph Brent Staubach

IPC: F25B9/00 ,  F02C3/04 ,  F02C7/18 ,  F02C7/224 ,  F02C7/22 ,  F25B9/06 ,  F25B40/02

Abstract: A gas turbine engine has a compressor section, a combustor, and a turbine section. An associated fluid is to be cooled and an associated fluid is to be heated. A transcritical vapor cycle heats the fluid to be heated, and cools the fluid to be cooled. The transcritical vapor cycle includes a gas cooler in which the fluid to be heated is heated by a refrigerant in the transcritical vapor cycle. An evaporator heat exchanger at which the fluid to be cooled is cooled by the refrigerant in the transcritical vapor cycle. A compressor upstream of the gas cooler compresses the refrigerant to a pressure above a critical point for the refrigerant. An expansion device expands the refrigerant downstream of the gas cooler, with the evaporator heat exchanger being downstream of the expansion device, and such that the refrigerant passing through the gas cooler to heat the fluid to be heated is generally above the critical point.