公开(公告)号：US20170276010A1

公开(公告)日：2017-09-28

申请号：US15606522

申请日：2017-05-26

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

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 driving a fan having fan blades supported by a fan shaft support defining a fan shaft support lateral and transverse stiffness. A gear system connected to the fan shaft including a ring gear defining a ring gear lateral and transverse stiffness, a gear mesh defining a gear mesh lateral and transverse stiffness, and a reduction ratio greater than 2.3. At least one of the ring gear lateral and transverse stiffness is less than 12% of a respective one of the gear mesh lateral and transverse stiffness. A flexible support supports the gear system and defines a flexible support lateral and transverse stiffness. At least one of the flexible support lateral and transverse stiffness is less than 11% of a respective one of the fan shaft support lateral and transverse stiffness.

公开(公告)号：US20170268426A1

公开(公告)日：2017-09-21

申请号：US15074829

申请日：2016-03-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/14 ,  F02C7/04 ,  F28F9/013 ,  F02C7/32 ,  F28D7/00 ,  F28D7/06

CPC classification number: F02C7/32 ,  F02C6/08 ,  F02C7/141 ,  F02C7/185 ,  F02K3/115 ,  F04D29/5826 ,  F05D2260/213 ,  F05D2300/175 ,  F28D7/06 ,  F28D2021/0026 ,  F28F9/002 ,  F28F9/0246 ,  F28F2255/02 ,  F28F2265/26 ,  F28F2280/00 ,  Y02T50/675

Abstract: A heat exchanger (HEX) arrangement for cooling air in a gas turbine engine is provided. The HEX arrangement may include a heat exchanger coupled to a plurality of ducts comprising a hot-side inlet duct and a hot-side outlet duct. The hot-side outlet duct may be in fluid communication with a compressor section of the gas turbine engine and in mechanical communication with a diffuser case. The HEX arrangement may further include a plurality of supporting links coupled between the heat exchanger and the gas turbine engine for securing the heat exchanger relative to the gas turbine engine. The supporting links may comprise a statically determined system. A spring rate ratio of between 1% and 30% may exist between the plurality of ducts and the plurality of supporting links.

公开(公告)号：US20170248082A1

公开(公告)日：2017-08-31

申请号：US15595234

申请日：2017-05-15

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Lawrence E. Portlock ,  Frederick M. Schwarz

IPC: F02C7/36 ,  F16H1/28

CPC classification number: F02C7/36 ,  F01D5/027 ,  F02C3/107 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/4031 ,  F05D2260/40311 ,  F16H1/28 ,  F16H57/0423 ,  F16H57/0486 ,  F16H2057/085

Abstract: An epicyclic gear train includes a carrier that supports star gears that mesh with a sun gear. A ring gear surrounds and meshes with the star gears. The star gears are supported on respective journal bearings. Each of the journal bearings includes a peripheral journal surface and each of the star gears includes a radially inner journal surface that is in contact with the peripheral journal surface of the respective journal bearing.

公开(公告)号：US20170241280A1

公开(公告)日：2017-08-24

申请号：US15052437

申请日：2016-02-24

Applicant: United Technologies Corporation

Inventor： Jeffrey D. Ponchak ,  Frederick M. Schwarz ,  David L. Motto

IPC: F01D11/00 ,  F16J15/06

CPC classification number: F01D11/003 ,  F01D11/005 ,  F01D25/246 ,  F05D2240/55 ,  F05D2240/57 ,  F16J15/067 ,  F16J15/0887

Abstract: A seal assembly for a gas turbine engine includes first and second split-ring seals. The first split-ring seal includes circumferentially separated first and second ends, laterally separated first and second edges, a first sealing lobe adjacent the first edge, and a first integral clip portion adjacent the second edge. The first sealing lobe has a curved surface extending laterally outward from the first edge. The second split-ring seal is slidably received and nested in the first seal. The second split-ring seal includes circumferentially separated third and fourth ends and laterally separated third and fourth edges.

公开(公告)号：US20170234236A1

公开(公告)日：2017-08-17

申请号：US15042382

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： Matthew R. Feulner ,  Frederick M. Schwarz

IPC: F02C7/277 ,  F02C9/00

CPC classification number: F02C7/277 ,  F01D19/02 ,  F02C7/18 ,  F02C9/00 ,  F05D2260/20 ,  F05D2260/85 ,  F05D2260/96 ,  F05D2270/02 ,  F05D2270/114 ,  Y02T50/676

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：US20170234159A1

公开(公告)日：2017-08-17

申请号：US15478671

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: F01D25/16 ,  F04D25/04 ,  F02C7/36 ,  F01D5/06 ,  F01D9/04 ,  F04D29/32 ,  F04D19/02

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, a compressor section, 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. 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：US09732629B2

公开(公告)日：2017-08-15

申请号：US14207722

申请日：2014-03-13

Applicant: United Technologies Corporation

Inventor： William G. Sheridan ,  Frederick M. Schwarz

IPC: F02C7/06 ,  F01D25/16 ,  F02C7/36 ,  F02C3/107 ,  F01D5/02

CPC classification number: F01D25/16 ,  F01D5/02 ,  F01D25/162 ,  F02C3/107 ,  F02C7/06 ,  F02C7/36 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/52 ,  F05D2240/54 ,  F05D2260/40311

Abstract: A turbofan engine (20; 300; 400) comprises a fan (28), a fan drive gear system (60), a fan shaft (120) coupling the fan drive gear system to the fan, a low spool, an intermediate spool, and a core spool. The low spool engages at least three main bearings of which at least two are non-thrust bearings and at least one is a thrust bearing. The fan shaft engages at least two bearings (148, 150). The core spool engages at least two bearings (250, 260). The intermediate spool engages at least two of said bearings (220, 200, 230; 220, 200, 230-2; 200, 220, 230-3).

公开(公告)号：US20170175761A1

公开(公告)日：2017-06-22

申请号：US14974151

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel L. Gysling

IPC: F04D29/32 ,  F02K3/06 ,  F04D29/66 ,  F04D29/52 ,  F02C7/36 ,  F04D19/00 ,  F04D29/38

Abstract: A gas turbine engine comprises a fan rotor having fan blades received within an outer nacelle. The fan blades are provided with at least a first type having a first natural frequency, and a second type having a second natural frequency. The fan rotor has a first mount structure intended for the first type and a distinct second mount structure intended for the second type. The first type of fan blade fits into the first mount structure intended for the first type, but there is a first obstruction preventing the first type of fan blade from being placed into the second mount structure intended for the second type. The second type of fan blade fits into the second mount structure intended for the second type, but there is a second obstruction preventing the second type of fan blade from being placed into the first mount structure intended for the first type.

公开(公告)号：US20170145852A1

公开(公告)日：2017-05-25

申请号：US14949448

申请日：2015-11-23

Applicant: United Technologies Corporation

Inventor： Michael E. McCune ,  Frederick M. Schwarz

IPC: F01D21/00 ,  F02C7/36 ,  F02C3/04

CPC classification number: F01D21/003 ,  F02C3/04 ,  F02C7/36 ,  F05D2220/32 ,  F05D2270/334 ,  G01H1/003 ,  G01M13/021 ,  G01M13/028

Abstract: A method of monitoring engine health is provided. The method may include the step of monitoring a vibration of a gearbox using a vibration sensor to detect a primary amplitude at a primary mesh frequency and a sideband amplitude at a sideband frequency. The method may further include calculating a ratio of the primary amplitude to the sideband amplitude, and evaluating a health of the gearbox based on the ratio of the primary amplitude to the sideband amplitude.

公开(公告)号：US20170130732A1

公开(公告)日：2017-05-11

申请号：US14934303

申请日：2015-11-06

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Jorn A. Glahn

IPC: F04D29/08 ,  F04D29/58 ,  F04D29/52 ,  F04D29/32 ,  F04D29/54

CPC classification number: F04D29/083 ,  F01D11/001 ,  F01D11/02 ,  F04D29/324 ,  F04D29/522 ,  F04D29/542 ,  F04D29/582 ,  F05D2220/32 ,  F05D2220/3219

Abstract: A gas turbine engine compressor section has a hub carrying a last row of compressor blades. A compressor exit guide vane is downstream of the last row of compressor blades. A housing is radially inward of the compressor exit guide vane. A non-contact seal is positioned on one of the housing and the hub.