公开(公告)号：US11585276B2

公开(公告)日：2023-02-21

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：US10704468B2

公开(公告)日：2020-07-07

申请号：US14771069

申请日：2014-02-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann

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

Abstract: A gas turbine engine is provided comprising 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 is in communication with said mid-span pre-diffuser inlet and said compressor section.

公开(公告)号：US10473037B2

公开(公告)日：2019-11-12

申请号：US15601563

申请日：2017-05-22

Applicant: United Technologies Corporation

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

IPC: F01D9/06 ,  F02C9/18 ,  F02C7/18 ,  F02C6/08

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, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.

公开(公告)号：US20190226351A1

公开(公告)日：2019-07-25

申请号：US16368150

申请日：2019-03-28

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William K. Ackermann

IPC: F01D11/02 ,  F01D11/00 ,  F16J15/44

Abstract: An assembly is provided for rotational equipment. The assembly includes a circumferentially segmented stator and a rotor radially within the stator. The assembly also includes a seal assembly configured for substantially sealing a gap radially between the stator and the rotor. The seal assembly includes a carrier and a non-contact seal seated with the carrier. The carrier includes a plurality of discrete carrier segments circumferentially arranged around the non-contact seal.

公开(公告)号：US10337406B2

公开(公告)日：2019-07-02

申请号：US14771047

申请日：2014-02-28

Applicant: United Technologies Corporation

Inventor： Gabriel L. Suciu ,  William K. Ackermann

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

Abstract: A gas turbine engine 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 is in communication with said mid-span pre-diffuser inlet and a bearing compartment.

公开(公告)号：US10240526B2

公开(公告)日：2019-03-26

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 ,  F02C7/36 ,  F02C9/16 ,  F02K3/06 ,  F02C3/06 ,  F02K3/072

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：US20180334966A1

公开(公告)日：2018-11-22

申请号：US15601563

申请日：2017-05-22

Applicant: United Technologies Corporation

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

IPC: F02C9/18 ,  F02C7/18 ,  F01D9/06

CPC classification number: F02C9/18 ,  F01D9/065 ,  F02C6/08 ,  F02C7/18 ,  F05D2260/20 ,  F05D2260/50 ,  F05D2270/3015

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, a bleed duct configured to convey the bleed airflow from the two or more bleed ports to the bleed outlet, and a delta-pressure valve located at each bleed port of the two or more bleed ports configured to move between an opened position and a closed position in response to a difference between a first pressure upstream of the delta-pressure valve and a second pressure downstream of the delta pressure valve. The bleed airflow is selectably conveyed through a bleed port of the two or more bleed ports depending on the operation of the associated delta-pressure valve.

公开(公告)号：US20180334962A1

公开(公告)日：2018-11-22

申请号：US15601499

申请日：2017-05-22

Applicant: United Technologies Corporation

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

IPC: F02C7/18

CPC classification number: F02C7/18 ,  F01P2023/00 ,  F01P2025/04 ,  F01P2025/08 ,  F02C6/08 ,  F02C7/057 ,  F02C9/18 ,  F05D2270/301 ,  F05D2270/303 ,  F16K31/00

Abstract: A bleed air cooling system for a gas turbine engine includes a bleed port located at an axial location of the gas turbine engine to divert a bleed airflow from a gas turbine engine flowpath, a bleed outlet located at a cooling location of the gas turbine engine and a bleed duct in fluid communication with the bleed port and the configured to convey the bleed airflow from the bleed port to the bleed outlet. A modulating valve is located at the bleed duct and is movable between a fully open position and a fully closed position to regulate the bleed airflow through the bleed duct based on one or more operating conditions of the gas turbine engine.

公开(公告)号：US10094241B2

公开(公告)日：2018-10-09

申请号：US14830514

申请日：2015-08-19

Applicant: United Technologies Corporation

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

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：US20180119563A1

公开(公告)日：2018-05-03

申请号：US15856421

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 drivingly 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 said ring gear transverse stiffness is less than 12% of a respective one of the gear mesh lateral stiffness and the gear mesh transverse stiffness.