公开(公告)号：US11598223B2

公开(公告)日：2023-03-07

申请号：US16227271

申请日：2018-12-20

Applicant: United Technologies Corporation

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

IPC: F01D25/16 ,  F02K3/06 ,  F02C3/107 ,  F01D15/12 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. The second turbine has a second exit area at a second exit point and is rotatable at a second speed. A first performance quantity is defined as the product of the first speed squared and the first area. A second performance quantity is defined as the product of the second speed squared and the second area.

公开(公告)号：US11459906B2

公开(公告)日：2022-10-04

申请号：US15601544

申请日：2017-05-22

Applicant: United Technologies Corporation

Inventor： Jonathan Ortiz ,  William K. Ackermann ,  Matthew P. Forcier

IPC: F01D21/00 ,  F01D25/12 ,  F02C7/12 ,  F02C9/18 ,  F01D17/10 ,  F01D17/14 ,  F01D5/02 ,  F04D27/00

Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, and a bleed duct in fluid communication with the bleed ports and configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet. A valve is located at each bleed port of and is configured to move between an opened position and a closed position, and one or more sensors are located along the bleed flowpath to sense one or more conditions of the bleed air cooling system. The valve at a particular bleed port is moved to the opened position based on the sensed one or more conditions.

公开(公告)号：US11286852B2

公开(公告)日：2022-03-29

申请号：US16568525

申请日：2019-09-12

Applicant: United Technologies Corporation

Inventor： William K. Ackermann ,  Peter M. Munsell

IPC: F02C6/08 ,  F01D25/12 ,  F02C7/18 ,  F01D11/04 ,  F01D25/16 ,  F02C7/06 ,  F02C7/28 ,  F02C9/18

Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.

公开(公告)号：US10927763B2

公开(公告)日：2021-02-23

申请号：US15091186

申请日：2016-04-05

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Kurt J. Sobanski ,  William K. Ackermann

IPC: F02C7/00 ,  F02C7/18 ,  F02K3/065 ,  F02C7/32 ,  F02C9/18 ,  F01D25/12 ,  F02K3/06

Abstract: A low pressure compressor for a gas turbine engine includes a low pressure compressor case extending circumferentially around a central axis of the gas turbine engine. The low pressure compressor case includes an inner radial wall surrounding a low pressure compressor rotor and an outer radial wall at least partially defining a fan bypass passage of the gas turbine engine. A low pressure compressor compartment is located between the inner radial wall and the outer radial wall and an electrical component is located in the low pressure compressor compartment. An inlet port at the outer radial wall is configured to admit a cooling airflow into the low pressure compressor compartment from the fan bypass passage to cool the electrical component.

公开(公告)号：US10760491B2

公开(公告)日：2020-09-01

申请号：US14771055

申请日：2014-02-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F01D17/10 ,  F02C6/08 ,  F01D9/04 ,  F01D9/06 ,  F02C7/06 ,  F02C7/14 ,  F01D5/02 ,  F02C3/04 ,  F02C7/04 ,  F01D25/24 ,  F04D29/54 ,  F01D25/12

Abstract: A gas turbine engine is provided that includes a compressor section, a combustor section, a diffuser case module, and a manifold. The diffuser case module includes a multiple of struts within an annular flow path from said compressor section to said combustor section, wherein at least one of said multiple of struts defines a mid-span pre-diffuser inlet in communication with said annular flow path. The manifold in communication with said mid-span pre-diffuser inlet and said combustor section.

公开(公告)号：US20200049077A1

公开(公告)日：2020-02-13

申请号：US16598048

申请日：2019-10-10

Applicant: United Technologies Corporation

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

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D25/16 ,  F01D5/06 ,  F02C3/06 ,  F02C7/06 ,  F04D29/32

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. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

公开(公告)号：US10330010B2

公开(公告)日：2019-06-25

申请号：US14967518

申请日：2015-12-14

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler ,  William K. Ackermann ,  Matthew R. Feulner ,  Om P. Sharma

IPC: F02C7/18 ,  F02C7/143 ,  F02C9/18 ,  F02C3/04 ,  F02K3/06 ,  F01D5/08 ,  F04D29/58

Abstract: A compressor section for use in a gas turbine engine comprises a compressor rotor having a hub and a plurality of blades extending radially outwardly from the hub and an outer housing surrounding an outer periphery of the blades. A tap taps air at a radially outer first location, passing the tapped air through a heat exchanger, and returning the tapped air to an outlet at a second location which is radially inward of the first location, to provide cooling air adjacent to the hub. A gas turbine engine is also disclosed.

公开(公告)号：US20180334918A1

公开(公告)日：2018-11-22

申请号：US15601544

申请日：2017-05-22

Applicant: United Technologies Corporation

Inventor： Jonathan Ortiz ,  William K. Ackermann ,  Matthew P. Forcier

IPC: F01D17/10 ,  F01D17/14 ,  F01D5/02 ,  F04D27/00 ,  F01D21/00 ,  F01D25/12

CPC classification number: F01D17/105 ,  F01D5/02 ,  F01D17/145 ,  F01D21/003 ,  F01D25/12 ,  F02C7/12 ,  F02C9/18 ,  F04D27/009 ,  F05D2220/32 ,  F05D2260/606

Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed flowpaths operably connected to a bleed outlet to divert a bleed airflow from a gas turbine engine flowpath. Each bleed flowpath includes two or more bleed ports to divert a bleed airflow from a gas turbine engine flowpath, and a bleed duct in fluid communication with the bleed ports and configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet. A valve is located at each bleed port of and is configured to move between an opened position and a closed position, and one or more sensors are located along the bleed flowpath to sense one or more conditions of the bleed air cooling system. The valve at a particular bleed port is moved to the opened position based on the sensed one or more conditions.

公开(公告)号：US20180252162A1

公开(公告)日：2018-09-06

申请号：US15970516

申请日：2018-05-03

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nathan Snape ,  Gabriel L. Suciu ,  Brian D. Merry ,  James D. Hill ,  William K. 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：US10047677B2

公开(公告)日：2018-08-14

申请号：US14755036

申请日：2015-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Jorn A. Glahn ,  Clifton J. Crawley, Jr. ,  Philip S. Stripinis ,  William K. Ackermann

IPC: F02C9/18 ,  F02C7/18 ,  F02C6/08 ,  F01D11/04 ,  F01D25/16 ,  F02C7/06 ,  F02C7/12 ,  F02C7/28 ,  F01D25/00

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a compressor section, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. A buffer system includes a first circuit that supplies a first buffer supply air and a second circuit that supplies a second buffer supply air. The first circuit includes a first bleed air supply and a second bleed air supply. The second circuit includes a third bleed air supply and a fourth bleed air supply and at least one of the first circuit and the second circuit includes a variable area ejector.