公开(公告)号：US20190291877A1

公开(公告)日：2019-09-26

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: B64D13/08 ,  F02C7/16 ,  F02C7/141

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：US10378374B2

公开(公告)日：2019-08-13

申请号：US14672561

申请日：2015-03-30

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F01D25/24 ,  F01D25/14 ,  F01D17/00 ,  F02C5/12 ,  F01D11/24 ,  F02C7/25

Abstract: A gas turbine engine includes a fluid intake. A turbine section includes a turbine case. A firewall is located upstream of the turbine section. A conduit is configured to direct a fluid from the fluid intake to the turbine case. A valve is located on a first side of the firewall opposite from the turbine section and is configured to regulate a flow of the fluid through the conduit.

公开(公告)号：US20190017405A1

公开(公告)日：2019-01-17

申请号：US16141372

申请日：2018-09-25

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Nathan Snape

IPC: F01D11/14 ,  F02C7/25 ,  F01D11/24 ,  F01D17/00 ,  F01D25/14 ,  F01D25/24 ,  F02C5/12

Abstract: An active clearance control assembly for a gas turbine engine includes a firewall, a fluid intake and an active clearance control manifold. A conduit is configured to direct a fluid from the fluid intake on a first axial side of the firewall through the firewall to at least one active clearance control manifold on a second axial side of the firewall. A valve is located on the first axial side of the firewall and is configured to regulate the flow of the fluid through the conduit.

公开(公告)号：US20180313266A1

公开(公告)日：2018-11-01

申请号：US16027496

申请日：2018-07-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Nathan Snape ,  Christopher M. Dye

IPC: F02C3/04 ,  F02C7/14 ,  F01D25/12 ,  F02C7/32 ,  F02C7/06 ,  F02C7/12 ,  F01D25/18

CPC classification number: F02C3/04 ,  F01D25/12 ,  F01D25/18 ,  F02C7/06 ,  F02C7/12 ,  F02C7/14 ,  F02C7/32

Abstract: A gas turbine engine includes an engine static structure housing that includes a compressor section and a turbine section. A combustor section is arranged axially between the compressor section and the turbine section. A core nacelle encloses the engine static structure to provide a core compartment. An oil tank is arranged in the core compartment and is axially aligned with the compressor section. A heat exchanger is secured to the oil tank and arranged in the core compartment.

公开(公告)号：US20180306043A1

公开(公告)日：2018-10-25

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

CPC classification number: F01D9/065 ,  F01D1/02 ,  F01D5/02 ,  F01D9/02 ,  F01D25/12 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32 ,  F05D2220/30 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/675

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：US10082078B2

公开(公告)日：2018-09-25

申请号：US14667975

申请日：2015-03-25

Applicant: United Technologies Corporation

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

IPC: F02C7/14

CPC classification number: F02C7/14 ,  F05D2260/213 ,  F05D2260/232 ,  F05D2260/98 ,  Y02T50/671 ,  Y02T50/675

Abstract: An aircraft thermal management system includes a first fluid system containing a first fluid, a fluid loop containing a thermally neutral heat transfer fluid, a second fluid system containing a second fluid, a first heat exchanger configured to transfer heat from the first fluid to the thermally neutral heat transfer fluid, and a second heat exchanger configured to transfer heat from the thermally neutral heat transfer fluid to the second fluid. The fluid loop is configured to provide the thermally neutral heat transfer fluid to the first heat exchanger at a pressure that matches the pressure of the first fluid.

公开(公告)号：US10006370B2

公开(公告)日：2018-06-26

申请号：US14745539

申请日：2015-06-22

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Brian D. Merry ,  Nathan Snape

IPC: F01D25/08 ,  F02C7/18

CPC classification number: F02C7/18 ,  F05D2260/213 ,  Y02T50/676

Abstract: A gas turbine engine comprises a main compressor section having a high pressure compressor with a downstream discharge, and more upstream locations. A turbine section has a high pressure turbine. A tap taps air from at least one of the more upstream locations in the compressor section, passes the tapped air through a heat exchanger and then to a cooling compressor. The cooling compressor compresses air downstream of the heat exchanger, and delivers air into the high pressure turbine. A core housing has an outer peripheral surface and a fan housing defining an inner peripheral surface. At least one bifurcation duct extends between the outer peripheral surface to the inner peripheral surface. The heat exchanger is received within the at least one bifurcation duct.

公开(公告)号：US10006302B2

公开(公告)日：2018-06-26

申请号：US14788345

申请日：2015-06-30

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 ,  F02C7/18 ,  F02C7/32 ,  F02C7/047 ,  F02C7/04

CPC classification number: F01D9/065 ,  F01D1/02 ,  F01D5/02 ,  F01D9/02 ,  F01D25/12 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32 ,  F05D2220/30 ,  F05D2260/20 ,  F05D2260/213 ,  Y02T50/675

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：US20180128178A1

公开(公告)日：2018-05-10

申请号：US15806992

申请日：2017-11-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan Snape ,  Joseph Brent Staubach ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F02C9/18 ,  B64D13/08

CPC classification number: F02C7/18 ,  B64D13/08 ,  B64D2013/0644 ,  F02C6/08 ,  F02C9/18 ,  F05D2260/213 ,  Y02T50/672 ,  Y02T50/676

Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.

公开(公告)号：US09920708B2

公开(公告)日：2018-03-20

申请号：US14617366

申请日：2015-02-09

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  Nathan Snape ,  Anthony R. Bifulco ,  William K. Ackermann ,  Becky E. Rose ,  Jesse M. Chandler

IPC: F02C7/04 ,  F02K1/04 ,  F01D15/08 ,  F01D25/14 ,  F02C7/057 ,  F02C7/18 ,  F01D25/12 ,  F02C7/14

CPC classification number: F02K1/04 ,  F01D15/08 ,  F01D25/12 ,  F01D25/125 ,  F01D25/14 ,  F02C7/04 ,  F02C7/047 ,  F02C7/057 ,  F02C7/14 ,  F02C7/18 ,  F02C7/185 ,  F02C7/32 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2260/213

Abstract: A nose cone assembly for a gas turbine engine and method of circulating air in a gas turbine engine are disclosed. The nose cone assembly includes a nose cone having an aperture communicating air to an interior space of the nose cone and a discharge member communicating the air out of the nose cone.