公开(公告)号：US10196930B2

公开(公告)日：2019-02-05

申请号：US14974808

申请日：2015-12-18

Applicant: United Technologies Corporation

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

IPC: F01D25/10 ,  F01D25/12 ,  F02K3/115 ,  F02C7/18 ,  F02C7/32 ,  F02C3/04

Abstract: The present disclosure relates generally to a gas turbine engine that includes a fan configured to generate a fanstream and a fanstream duct configured to receive the fanstream flowing therethrough. An engine electronic component is positioned in flow communication with the fanstream. A heating element is positioned in the fanstream upstream from the engine electronic component and is operative to heat at least a portion of the fanstream in flow communication with the engine electronic component. The position of the engine electronic component passively thermally conditions the engine electronic component and the heating element actively thermally conditions the engine electronic component.

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：US10100738B2

公开(公告)日：2018-10-16

申请号：US14600862

申请日：2015-01-20

Applicant: United Technologies Corporation

Inventor： James D. Hill ,  William K. Ackermann

IPC: F02C7/18 ,  F02C3/04 ,  F01D25/12 ,  F02K3/115 ,  F02C6/06 ,  F23R3/04 ,  F02C6/08 ,  F01D9/02 ,  F02C9/18 ,  F02C7/12 ,  F01D5/08

Abstract: A cooling system is provided. The cooling system may comprise a heat exchanger and a first conduit fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the first conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage. A gas turbine engine is also provided and may comprise a compressor, a combustor in fluid communication with the compressor, and a diffuser around the combustor and a turbine. A heat exchanger may have an inlet fluidly coupled to the diffuser. A second conduit may be fluidly coupled to an outlet of the heat exchanger. An annular passage may be fluidly coupled to the second conduit. A tangential onboard injector (TOBI) may be fluidly coupled to the annular passage.

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：US09988943B2

公开(公告)日：2018-06-05

申请号：US14696615

申请日：2015-04-27

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： James P. Chasse, Jr. ,  Ryan K. Snyder ,  William K. Ackermann ,  Pellegrino J. Pisacreta ,  Judith F. Brooks ,  Stephanie Ernst

IPC: F01D25/12 ,  F01D25/28 ,  F02C7/18 ,  F01D25/14

CPC classification number: F01D25/28 ,  F01D25/12 ,  F01D25/14 ,  F02C7/18 ,  Y02T50/675

Abstract: A fitting according to an exemplary aspect of the present disclosure includes, among other things, a main body portion having a first axial end and a second axial end opposite the first axial end, an inlet provided at the first axial end, and an outlet adjacent the second axial end. The outlet includes a plurality of circumferentially spaced-apart slots formed through the main body portion, and each slot has an area within a range of 0.52 and 0.59 square inches.

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.

公开(公告)号：US20180045138A1

公开(公告)日：2018-02-15

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

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.

公开(公告)号：US20170370285A1

公开(公告)日：2017-12-28

申请号：US15682848

申请日：2017-08-22

Applicant: United Technologies Corporation

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

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

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 compressor section is in fluid communication with a fan, which includes a first compressor section and a second compressor section. A turbine section includes a first turbine section driving the fan and the first compressor section and a second turbine section driving the second compressor section and the second compressor rotor. 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. A performance ratio of the first performance quantity to the second performance quantity is between about 0.2 and about 0.8. A gear reduction is included between the first turbine section and the first compressor section.

公开(公告)号：US09845726B2

公开(公告)日：2017-12-19

申请号：US14568167

申请日：2014-12-12

Applicant: United Technologies Corporation

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

IPC: F02C3/06 ,  F02C7/36 ,  F02K3/02 ,  F02K3/06 ,  F02C3/04 ,  F02K3/04 ,  F02K3/072

CPC classification number: F02C3/06 ,  F02C3/04 ,  F02C7/36 ,  F02K3/02 ,  F02K3/04 ,  F02K3/06 ,  F02K3/072 ,  F05D2220/3215

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.

公开(公告)号：US20170298757A1

公开(公告)日：2017-10-19

申请号：US15638954

申请日：2017-06-30

Applicant: UNITED TECHNOLOGIES CORPORATION

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

IPC: F01D15/12 ,  F04D19/00 ,  F04D29/053 ,  F01D5/06 ,  F04D25/04 ,  F02K3/06

CPC classification number: F01D15/12 ,  F01D5/06 ,  F01D9/041 ,  F02C3/107 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/002 ,  F04D25/045 ,  F04D29/053 ,  F04D29/325 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/60 ,  F05D2260/4031 ,  F05D2260/40311 ,  F05D2300/501 ,  Y02T50/671

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan shaft driving a fan having fan blades. A fan shaft support supports the fan shaft and a gear system is connected to the fan shaft. The gear system includes a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness and a reduction ratio greater than 2.3. A gear system input to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness. At least one of said gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of said gear mesh lateral stiffness and said gear mesh transverse stiffness.