公开(公告)号：US10669888B2

公开(公告)日：2020-06-02

申请号：US16107270

申请日：2018-08-21

Applicant: United Technologies Corporation

Inventor： William K. Ackermann ,  Clifton J. Crawley, Jr. ,  Frederick M. Schwarz

IPC: F01D25/12 ,  F01D5/08 ,  F01D5/30 ,  F01D11/00 ,  F16J15/44 ,  F01D5/02 ,  F01D9/04 ,  F01D11/04 ,  F01D11/08 ,  F02C3/14 ,  F02C7/18

Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a bladed rotor assembly, a stator vane assembly, a fixed stator structure and a seal assembly. The bladed rotor assembly includes a rotor disk structure. The stator vane assembly is disposed adjacent the bladed rotor assembly. The fixed stator structure is connected to and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.

公开(公告)号：US10415478B2

公开(公告)日：2019-09-17

申请号：US15332249

申请日：2016-10-24

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  James D. Hill ,  William K. Ackermann

IPC: F02C7/18 ,  F02C3/04 ,  F01D5/08 ,  F02C6/18 ,  F23R3/04 ,  F01D9/02 ,  F02C6/08

Abstract: Air mixing systems for gas turbine engines include a heat exchanger, a first extraction conduit fluidly coupled to an inlet of the heat exchanger, a second extraction conduit fluidly coupled to an outlet of the heat exchanger, an injection conduit fluidly coupled to the second extraction conduit, an onboard injector supply chamber fluidly coupled to the injection conduit, and an onboard injector fluidly coupled to the onboard injector supply chamber.

公开(公告)号：US10352241B2

公开(公告)日：2019-07-16

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

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：US20190186357A1

公开(公告)日：2019-06-20

申请号：US16282891

申请日：2019-02-22

Applicant: United Technologies Corporation

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

IPC: F02C3/113 ,  F02K3/072 ,  F02C9/16 ,  F02K3/06 ,  F02C3/06 ,  F02C7/36

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 turbofan engine according to an example of the present disclosure includes, among other things, a fan including fan blades, an outer housing that surrounds the fan to define a bypass flow path, a compressor section in fluid communication with the fan, the compressor section including a low pressure compressor section and a high pressure compressor section, a turbine section including a fan drive turbine section driving the fan and the low pressure compressor section and a high pressure turbine section driving the high pressure compressor section. A gear reduction including an epicyclic gear train is between the fan drive turbine section and the low pressure compressor section such that the low pressure compressor section and the fan are rotatable at a common speed and such that the fan is rotatable at a lower speed than the fan drive turbine section. The fan drive turbine section has a first exit area at a first exit point and is rotatable at a first speed, the high pressure turbine section has a second exit area at a second exit point and is rotatable at a second speed, which is higher than the first speed. 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 and a performance ratio of the first performance quantity to the second performance quantity is between 0.2 and 0.8.

公开(公告)号：US10287914B2

公开(公告)日：2019-05-14

申请号：US15478706

申请日：2017-04-04

Applicant: United Technologies Corporation

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

IPC: F01D15/12 ,  F01D25/16 ,  F04D25/04 ,  F04D25/02 ,  F04D27/00 ,  F04D29/32 ,  F04D19/02 ,  F01D5/06 ,  F01D9/04 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06 ,  F02C3/04

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, 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. A mid-turbine frame is positioned intermediate the fan drive turbine and the second turbine, and can include a bearing support. 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：US20190107055A1

公开(公告)日：2019-04-11

申请号：US16158581

申请日：2018-10-12

Applicant: United Technologies Corporation

Inventor： Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/18 ,  F02K3/06 ,  F01D25/08 ,  F01D5/08 ,  F01D5/02 ,  F02C7/36 ,  F02C7/12 ,  F02C6/08

Abstract: A gas turbine engine comprises a compressor section and a turbine section, with the turbine section having a first stage blade row and a downstream blade row. A higher pressure tap is tapped from a higher pressure first location in the compressor. A lower pressure tap is tapped from a lower pressure location in the compressor which is at a lower pressure than the first location. The higher pressure tap passes through a heat exchanger, and then is delivered to cool the first stage blade row in the turbine section. The lower pressure tap is delivered to at least partially cool the downstream blade row.

公开(公告)号：US20190003327A1

公开(公告)日：2019-01-03

申请号：US16123027

申请日：2018-09-06

Applicant: United Technologies Corporation

Inventor： William K. Ackermann ,  Clifton J. Crawley, JR. ,  Frederick M. Schwarz

IPC: F01D11/02 ,  F01D5/08 ,  F16J15/44 ,  F01D11/00 ,  F01D9/06 ,  F01D5/30 ,  F01D11/12 ,  F01D9/04

Abstract: Assemblies are provided for rotational equipment. One of these assemblies includes a first bladed rotor assembly, a second bladed rotor assembly, a stator vane assembly, a stator structure and a seal assembly. The second bladed rotor assembly includes a rotor disk structure. The stator vane assembly is axially between the first and the second bladed rotor assemblies. The stator structure is mated with and radially within the stator vane assembly. The seal assembly is configured for sealing a gap between the stator structure and the rotor disk structure, wherein the seal assembly includes a non-contact seal.

公开(公告)号：US20180135454A1

公开(公告)日：2018-05-17

申请号：US15856396

申请日：2017-12-28

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 ,  F04D25/04 ,  F02K3/06 ,  F04D29/053 ,  F01D5/06 ,  F04D19/00

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 drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system connected to the fan shaft. The gear system includes a ring gear defining a ring gear lateral stiffness and a ring gear transverse stiffness, a gear mesh defining a gear mesh lateral stiffness and a gear mesh transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral stiffness and the ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness the ring gear transverse stiffness.

公开(公告)号：US20180119564A1

公开(公告)日：2018-05-03

申请号：US15856441

申请日：2017-12-28

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 ,  F02K3/06 ,  F04D29/053 ,  F04D25/04 ,  F04D19/00 ,  F01D5/06

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 drivingly connected to a fan with the fan having fan blades. A fan shaft support that supports the fan shaft and a gear system 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 connected to the gear system defines a gear system input lateral stiffness and a gear system input transverse stiffness At least one of the gear system input lateral stiffness and said gear system input transverse stiffness is less than 5% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.

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.