公开(公告)号：US20180073392A1

公开(公告)日：2018-03-15

申请号：US15801611

申请日：2017-11-02

Applicant: United Technologies Corporation

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

IPC: F01D25/16 ,  F02C3/107 ,  F04D29/056 ,  F02C7/06 ,  F02C7/20 ,  F04D29/66 ,  F01D5/06 ,  F01D9/04

CPC classification number: F01D25/164 ,  F01D5/06 ,  F01D9/041 ,  F01D15/12 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02C7/20 ,  F02C7/36 ,  F02K3/06 ,  F04D19/02 ,  F04D25/028 ,  F04D25/045 ,  F04D29/056 ,  F04D29/325 ,  F04D29/668 ,  F05D2220/32 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan and a turbine section including a fan drive turbine and a second turbine. 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：US09915204B2

公开(公告)日：2018-03-13

申请号：US14676513

申请日：2015-04-01

Applicant: United Technologies Corporation

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

IPC: F01D5/08 ,  F02C7/18 ,  F01D11/00 ,  F01D25/24

CPC classification number: F02C7/18 ,  F01D5/088 ,  F01D11/001 ,  F01D25/24

Abstract: Systems and methods are disclosed herein for distributing cooling air in gas turbine engines. A tangential on board injector (“TOBI”) may supply cooling air to a turbine section of a gas turbine engine. The cooling air may be split into a first cooling air path and a second cooling air path. The first cooling air path may fluidly connect the TOBI and the interior of a first stage rotor blade. The second cooling air path may fluidly connect the TOBI and a cavity. The cavity may be located between a first disk and a second disk. The cooling air paths from a single cooling air source may thermally isolate portions of the turbine section.

公开(公告)号：US20180066587A1

公开(公告)日：2018-03-08

申请号：US15807911

申请日：2017-11-09

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  Jesse M. Chandler ,  Joseph Brent Staubach ,  Brian D. Merry ,  Wesley K. Lord

IPC: F02C7/18 ,  F02C3/13 ,  F02C7/143 ,  F01D25/12

Abstract: A gas turbine engine comprises a main compressor section having a downstream most end, 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 ng air downstream of the heat exchanger, and delivers air into the high pressure turbine. The heat exchanger has at least two passes, with one of the passes passing air radially outwardly, and a second of the passes returning the air radially inwardly to the compressor. An intercooling system for a gas turbine engine is also disclosed.

公开(公告)号：US09909497B2

公开(公告)日：2018-03-06

申请号：US14706748

申请日：2015-05-07

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Brian D. Merry ,  Jesse M. Chandler ,  Gabriel L. Suciu ,  Joseph B. Staubach

IPC: F02C6/08 ,  F04D27/02 ,  F02C7/052 ,  F04D29/52 ,  F04D29/70 ,  F02C3/10 ,  F02K3/06

CPC classification number: F02C6/08 ,  F02C3/10 ,  F02C7/052 ,  F02K3/06 ,  F04D27/0215 ,  F04D29/526 ,  F04D29/701 ,  F05D2210/12 ,  F05D2220/36 ,  F05D2260/607 ,  F05D2260/608 ,  F05D2270/101 ,  Y02T50/675

Abstract: A compressor section of a gas turbine engine includes a bleed port having a flow splitter therein so as to define a downstream bleed channel having a downstream inlet and an upstream bleed channel having an upstream inlet that is positioned radially outward from the downstream inlet.

公开(公告)号：US20180045120A1

公开(公告)日：2018-02-15

申请号：US15791825

申请日：2017-10-24

Applicant: United Technologies Corporation

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

IPC: F02C7/36 ,  F02K3/04 ,  F02C3/107 ,  F02C3/04 ,  F02K3/06

CPC classification number: F02C7/36 ,  F02C3/04 ,  F02C3/107 ,  F02K3/04 ,  F02K3/06

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：US20180045119A1

公开(公告)日：2018-02-15

申请号：US15232101

申请日：2016-08-09

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Gabriel L. Suciu ,  Michael E. McCune

IPC: F02C7/32 ,  F02C7/275 ,  F02N11/00 ,  F02K3/06

CPC classification number: F02C7/32 ,  F02C3/107 ,  F02C7/275 ,  F02K3/06 ,  F02N11/00 ,  F05D2220/327 ,  F05D2220/76 ,  F05D2260/532 ,  F05D2260/85 ,  F05D2260/98

Abstract: A geared turbofan engine includes a first spool including a first compressor and a first turbine. The first compressor is immediately before a combustor and the first turbine is immediately after the combustor. A second spool includes at least a second turbine disposed axially aft of the first turbine. A first tower shaft is engaged to drive the high speed spool. A second tower shaft engaged to be driven by the second spool. A starter is engaged to drive the first tower shaft. An accessory gear box is driven by the second tower shaft. A first clutch is disposed between the first tower shaft and the starter. The first clutch is configured to enable the starter to drive the high speed spool. A second clutch is disposed between the second tower shaft and the accessory gear box, the second clutch configured to enable the second spool to drive the accessory gear box. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

公开(公告)号：US20180038315A1

公开(公告)日：2018-02-08

申请号：US15230590

申请日：2016-08-08

Applicant: United Technologies Corporation

Inventor： Wesley K. Lord ,  Jesse M. Chandler ,  Gabriel L. Suciu

IPC: F02K3/00 ,  B64D33/04 ,  B64D33/02 ,  F02K1/52 ,  B64D27/14

CPC classification number: F02K3/00 ,  B64D27/14 ,  B64D33/02 ,  B64D33/04 ,  B64D35/04 ,  F02K1/52 ,  F02K3/062 ,  F05D2250/312

Abstract: A gas turbine engine includes a core engine assembly including a compressor section communicating air to a combustor section where the air is mixed with fuel and ignited to generate a high-energy gas flow that is expanded through a turbine section. The turbine section is coupled to drive the compressor section. A propulsor section aft of the core engine is driven by the turbine section. An exhaust duct routing exhaust gases around the propulsor section. The exhaust duct includes an inlet forward of the propulsor section, an outlet aft of the turbine section and a passageway between the inlet and the outlet. An aircraft and exhaust duct are also disclosed.

公开(公告)号：US20180023576A1

公开(公告)日：2018-01-25

申请号：US15218915

申请日：2016-07-25

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Arthur W. Utay ,  Tania Bhatia Kashyap ,  Thomas N. Slavens ,  Kevin L. Rugg ,  Mark F. Zelesky ,  Brian D. Merry ,  Gabriel L. Suciu

IPC: F04D17/10 ,  B64D41/00 ,  F04D29/42 ,  F04D29/02 ,  F04D29/28

CPC classification number: B64D41/00 ,  F02C3/08 ,  F02C3/145 ,  F04D17/105

Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.

公开(公告)号：US20180022459A1

公开(公告)日：2018-01-25

申请号：US14998001

申请日：2014-07-07

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: B64D13/06 ,  F02K3/04 ,  B64D27/26

CPC classification number: B64D13/06 ,  B64D27/26 ,  B64D2013/0603 ,  B64D2013/0618 ,  B64D2027/262 ,  F02C6/08 ,  F02C7/20 ,  F02K3/04

Abstract: A gas turbine engine includes a fan section delivering air into a compressor section. The compressor section compresses air and delivers air into a combustion section. Products of combustion pass from the combustion section over a turbine section to drive the fan section and main compressor sections. A gearbox is driven by the turbine section to drive the fan section. An environmental control system includes a higher pressure tap at a higher pressure location in the compressor section, and a lower pressure tap at a lower pressure location. The lower pressure location being at a lower pressure than the higher pressure location. The lower pressure tap communicates to a first passage leading to a downstream outlet, and having a second passage leading into a compressor section of a turbocompressor. The higher pressure tap leads into a turbine section of the turbocompressor such that air in the higher pressure tap drives the turbine section to in turn drive the compressor section of the turbocompressor. A combined outlet of the compressor section and the turbine section of the turbocompressor intermixes and passes downstream to be delivered to an aircraft use. A pylon supports the engine. The pylon defines a lowermost surface and the higher pressure tap extends above a plane including the lowermost surface. The higher pressure tap includes a double wall tube above the plane for preventing leakage from impinging on a portion of the pylon. An environmental control system is also disclosed.

公开(公告)号：US20170363099A1

公开(公告)日：2017-12-21

申请号：US15186739

申请日：2016-06-20

Applicant: United Technologies Corporation

Inventor： Stephen H. Taylor ,  Charles E. Lents ,  Gabriel L. Suciu ,  Brian D. Merry ,  Jesse M. Chandler

IPC: F04D27/02 ,  F01D15/08 ,  F01D17/14 ,  F04D29/32 ,  F01D5/02 ,  F04D25/06 ,  F04D27/00 ,  F01D15/12

Abstract: A gas turbine engine includes a main engine compressor section. A booster compressor changes a pressure of airflow received from the main engine compressor section to a pressure desired for a pneumatic system. The booster compressor is configured to operate at airflow conditions greater than a demand of the pneumatic system. An exhaust valve controls airflow between an exhaust outlet and an outlet passage to the pneumatic system. The exhaust valve is operable to exhaust airflow from the booster compressor in excess of the demand of the pneumatic system. A bleed air system for a gas turbine engine and a method of controlling engine bleed airflow are also disclosed.