公开(公告)号：US20160003149A1

公开(公告)日：2016-01-07

申请号：US14771069

申请日：2014-02-28

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/14 ,  F01D9/04 ,  F01D5/02 ,  F02C3/04 ,  F02C7/04

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.

Abstract translation: 提供了一种燃气涡轮发动机，其包括压缩机部分，燃烧器部分，扩散器壳体模块和歧管。 扩散器壳模块包括在从所述压缩机部分到所述燃烧器部分的环形流动路径内的多个支柱，其中所述多个支柱中的至少一个限定了与所述环形流动路径连通的中跨预扩散器入口。 歧管与所述中跨预扩散器入口和所述压缩机部分连通。

公开(公告)号：US20150096303A1

公开(公告)日：2015-04-09

申请号：US14573003

申请日：2014-12-17

Applicant: United Technologies Corporation

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

IPC: F02C3/04 ,  F02C7/36

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：US11168574B2

公开(公告)日：2021-11-09

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：US10823070B2

公开(公告)日：2020-11-03

申请号：US15410971

申请日：2017-01-20

Applicant: United Technologies Corporation

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

IPC: F02C7/18 ,  F02C3/04 ,  F02K3/06

Abstract: An intercooled cooling system for a gas turbine engine includes a heat exchanger in fluid communication with a cooling airflow source directed through the heat exchanger and an auxiliary compressor fluidly coupled to the heat exchanger via a discharge duct to compress the cooling airflow exiting the heat exchanger. A compressor discharge pathway directs a first portion of the cooling airflow from the auxiliary compressor to a first cooling location of the gas turbine engine, and a bypass pathway is fluidly coupled to the discharge duct between the heat exchanger and the auxiliary compressor to direct a second portion of the cooling airflow to a second cooling location of the gas turbine without passing through the auxiliary compressor.

公开(公告)号：US10808616B2

公开(公告)日：2020-10-20

申请号：US14771038

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, a turbine section, 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 turbine section.

公开(公告)号：US10753218B2

公开(公告)日：2020-08-25

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 ,  F01D1/02 ,  F01D25/12 ,  F01D5/02 ,  F01D9/02 ,  F02C7/04 ,  F02C7/047 ,  F02C7/18 ,  F02C7/32

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：US10731502B2

公开(公告)日：2020-08-04

申请号：US14877965

申请日：2015-10-08

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： William K. Ackermann ,  Matthew P. Forcier ,  Paul J. Hiester

IPC: F02C6/08 ,  F01D17/10 ,  F01D5/02 ,  F01D25/24 ,  F02C3/06 ,  F01D5/08 ,  F04D27/02 ,  F01D25/08 ,  F02C9/18

Abstract: A compressor for use in a gas turbine engine comprises a compressor rotor including blades and a disc, with a bore defined radially inwardly of the disc. A radially outer housing surrounds an outer diameter of the blades. A lower pressure tap and a higher pressure tap tap air from two distinct locations within the compressor and radially outwardly through the outer housing. A valve selectively delivers at least one of the lower pressure tap and the higher pressure tap to the bore of the disc. A control for the valve is programmed to move the valve to a position delivering the higher pressure tap at a point prior to take-off when the compressor is mounted in a gas turbine engine on an aircraft. A gas turbine engine and a method of operating a gas turbine engine are also disclosed.

公开(公告)号：US10358932B2

公开(公告)日：2019-07-23

申请号：US14754161

申请日：2015-06-29

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William K. Ackermann

IPC: F01D11/00 ,  F01D11/02 ,  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：US20180355756A1

公开(公告)日：2018-12-13

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

CPC classification number: F01D25/12 ,  F01D5/02 ,  F01D5/082 ,  F01D5/3015 ,  F01D9/041 ,  F01D11/001 ,  F01D11/04 ,  F01D11/08 ,  F02C3/14 ,  F02C7/18 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/55 ,  F16J15/442 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

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：US20180334965A1

公开(公告)日：2018-11-22

申请号：US15601524

申请日：2017-05-22

Applicant: United Technologies Corporation

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

IPC: F02C9/18 ,  F01D17/02 ,  F01D9/06 ,  F02C7/18

CPC classification number: F02C9/18 ,  F01D9/065 ,  F01D17/02 ,  F02C7/18 ,  F05D2220/32 ,  F05D2260/20 ,  F05D2270/30

Abstract: A bleed air cooling system for a gas turbine engine includes one or more bleed ports located at one or more axial locations 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. One or more safety sensors are configured to sense operational characteristics of the gas turbine engine, and a controller is operably connected to the one or more safety sensors and configured to evaluate the sensed operational characteristics for anomalies in operation of the bleed air cooling system.