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：US10125691B2

公开(公告)日：2018-11-13

申请号：US15042382

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Frederick M. Schwarz

IPC: F02C7/26 ,  F02C7/277 ,  F01D19/02 ,  F02C7/18 ,  F02C9/00

Abstract: A bowed rotor start mitigation system for a gas turbine engine is provided. The bowed rotor start mitigation system includes a variable position starter valve and a controller. The controller is operable to dynamically adjust the variable position starter valve to deliver a starter air supply to a starter to drive rotation of a starting spool of the gas turbine engine according to a dry motoring profile that continuously varies a rotor speed of the starting spool up to a point below a critical rotor speed.

公开(公告)号：US10119466B2

公开(公告)日：2018-11-06

申请号：US14950393

申请日：2015-11-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Karl L. Hasel

IPC: F02K3/06 ,  F02C3/13 ,  F02C7/36 ,  F02C3/06 ,  F02C3/10

Abstract: A gas turbine engine comprises a fan includes a plurality of fan blades rotatable about an axis. A compressor section includes at least a first compressor section and a second compressor section, wherein components of the second compressor section are configured to operate at an average exit temperature that is between about 1000° F. and about 1500° F. A combustor is in fluid communication with the compressor section. A turbine section is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.

公开(公告)号：US10107135B2

公开(公告)日：2018-10-23

申请号：US14922507

申请日：2015-10-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D15/12 ,  F01D21/00 ,  F02C3/04 ,  F02C7/06 ,  F16D11/00 ,  F16D11/16

Abstract: A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan and a braking system. The braking system is configured to selectively engage the fan during ground windmilling to apply a first level of braking to slow rotation of the fan. Further, when the rotation of the fan sufficiently slows, the braking system is further configured to apply a second level of braking more restrictive than the first level of braking.

公开(公告)号：US10107126B2

公开(公告)日：2018-10-23

申请号：US14830437

申请日：2015-08-19

Applicant: United Technologies Corporation

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

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

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：US10100745B2

公开(公告)日：2018-10-16

申请号：US14432377

申请日：2013-02-08

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/26 ,  F02C7/36 ,  F02C7/32 ,  F02C3/10 ,  F02C3/107 ,  F02C7/20

Abstract: An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.

公开(公告)号：US10094296B2

公开(公告)日：2018-10-09

申请号：US14761073

申请日：2014-02-11

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F02C1/00 ,  F02C9/18 ,  F02C3/06 ,  F01D5/08 ,  F01D25/10 ,  F02C7/28 ,  F01D19/00

Abstract: A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, and into the bore of the disk. A method is also disclosed.

公开(公告)号：US10093424B2

公开(公告)日：2018-10-09

申请号：US14998001

申请日：2014-07-07

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: B64D13/06 ,  B64D27/26 ,  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：US10060280B2

公开(公告)日：2018-08-28

申请号：US14884513

申请日：2015-10-15

Applicant: United Technologies Corporation

Inventor： Clifton J. Crawley, Jr. ,  Frederick M. Schwarz

IPC: F01D11/02 ,  F01D5/08 ,  F01D9/06 ,  F02C3/04

CPC classification number: F01D11/02 ,  F01D5/082 ,  F01D5/3015 ,  F01D9/065 ,  F01D11/001 ,  F02C3/04 ,  F05D2240/55 ,  F05D2240/81 ,  Y02T50/676

Abstract: Aspects of the disclosure are directed to a gas turbine engine, comprising a sealing assembly that includes a non-contacting HALO seal, a ring constructed as a full ring and configured as a carrier of the seal, a sealing land configured to rotate and interface to the seal. In some embodiments, the engine further comprises a vane, where the ring is coupled to the vane.

公开(公告)号：US10036316B2

公开(公告)日：2018-07-31

申请号：US14663727

申请日：2015-03-20

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Karl L. Hasel

IPC: F02K3/06 ,  F02C3/13 ,  F02C7/36 ,  F02C3/06 ,  F02C3/10

CPC classification number: F02C3/13 ,  F02C3/06 ,  F02C3/10 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2240/55 ,  F05D2250/283 ,  F05D2260/40311 ,  Y02T50/671

Abstract: A gas turbine engine includes a fan with a plurality of fan blades rotatable about an axis, and a compressor section that includes at least first and second compressor sections. An average exit temperature of the compressor section is between about 1000° F. and about 1500° F. The engine also includes a combustor that is in fluid communication with the compressor section, and a turbine section that is in fluid communication with the combustor. A geared architecture is driven by the turbine section for rotating the fan about the axis.