公开(公告)号：US10267228B2

公开(公告)日：2019-04-23

申请号：US14177372

申请日：2014-02-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02C1/00 ,  F02C3/107 ,  F02C7/36 ,  F02K3/06

Abstract: A gas turbine engine includes a fan section and a compressor section. The compressor section includes both a first compressor section and a second compressor section. A turbine section includes at least one turbine and driving the second compressor section and a fan drive turbine driving at least a gear arrangement to drive the fan section. A power ratio is provided by the combination of the first compressor section and the second compressor section, with the power ratio being provided by a first power input to the first compressor section and a second power input to the second compressor section, the power ratio being equal to, or greater than, about 1.0 and less than, or equal to, about 1.4.

公开(公告)号：US20190113003A1

公开(公告)日：2019-04-18

申请号：US16166235

申请日：2018-10-22

Applicant: United Technologies Corporation

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

IPC: F02K3/06 ,  F02C7/36

CPC classification number: F02K3/06 ,  F02C7/36 ,  F05D2220/323 ,  F05D2220/36 ,  F05D2240/70 ,  F05D2260/34 ,  F05D2260/4031 ,  F05D2260/40311 ,  F16H57/0479 ,  F16H57/0486

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a turbo fan shaft and a turbo fan supported on the fan shaft, a compressor section having compressor hubs with blades driven about an axis, and an epicyclic gear system driving the fan shaft. The gear system includes a carrier supporting intermediate gears that mesh with a sun gear, a ring gear surrounding and meshing with the intermediate gears, the ring gear including first and second portions each having an inner periphery with teeth, the first and second portions abutting one another at a radial interface, each of the first and second portions including a flange extending radially outward, and the first and second portions having grooves at the radial interface which form a hole that expels oil through the ring gear to a gutter, and an input shaft driving the fan shaft through the gear system, the input shaft connected to the sun gear.

公开(公告)号：US20190107058A1

公开(公告)日：2019-04-11

申请号：US16152710

申请日：2018-10-05

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

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

Abstract: An example gas turbine engine includes a propulsor assembly including a fan and a fan drive turbine. A weight of the propulsor assembly is less than about 40% of a total weight of the gas turbine engine.

公开(公告)号：US20190085771A1

公开(公告)日：2019-03-21

申请号：US16186795

申请日：2018-11-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F02C7/36 ,  F02C3/107 ,  F02K3/06

Abstract: A method is provided that includes providing a first turbine engine and providing a second turbine engine. The first turbine engine is configured with a first thrust rating. The first turbine engine includes a first engine rotating assembly and a first engine case structure housing at least the first engine rotating assembly. The second turbine engine is configured with a second thrust rating that is different than the first thrust rating. The second turbine engine includes a second engine rotating assembly and a second engine case structure housing at least the second engine rotating assembly. The first engine case structure and the second engine case structure have at least substantially common configurations. The first turbine engine and the second turbine engine are provided by a common entity.

公开(公告)号：US10234359B2

公开(公告)日：2019-03-19

申请号：US15161323

申请日：2016-05-23

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Marnie A. Rizo ,  David P. Houston ,  David M. Nissley ,  Paul J. Hiester ,  Timothy Dale ,  Timothy B. Winfield ,  Madeline N. Campbell ,  James R. Midgley

IPC: G06F11/30 ,  G01M15/14 ,  B64D27/10 ,  F02C9/00 ,  G05B23/02

Abstract: A method of monitoring a gas turbine engine includes the steps of: (a) receiving information from actual flights of an aircraft including an engine to be monitored, and including at least one of the ambient temperature at takeoff, and internal engine pressures, temperatures and speeds; (b) evaluating the damage accumulated on an engine component given the data received in step (a); (c) storing the determined damage from step (b); (d) repeating steps (a)-(c); (e) recommending a suggested future use for the component based upon steps (a)-(d). A system is also disclosed.

公开(公告)号：US10215027B2

公开(公告)日：2019-02-26

申请号：US14877254

申请日：2015-10-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Michael A. Weisse

IPC: F01D5/14 ,  B23K20/12 ,  F01D5/16 ,  B23K101/00

Abstract: An airfoil includes, among other possible things, a main body extending between a leading edge and a trailing edge. Channels are formed into the main body, with a plurality of ribs extending intermediate the channels. A cover skin is attached to the main body. The cover skin is welded to the main body with a weld at outer edges. An adhesive is placed between inner surfaces of the cover skin and the main body. The adhesive is deposited inwardly of the outer edges of the cover skin. A method of constructing an airfoil is also disclosed as is a gas turbine engine.

公开(公告)号：US20190055026A1

公开(公告)日：2019-02-21

申请号：US15681987

申请日：2017-08-21

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Nigel David Sawyers-Abbott ,  Frederick M. Schwarz

IPC: B64D27/26 ,  F02C7/20 ,  F01D25/28

Abstract: A turbofan engine may comprise an inlet and a fan case coupled to the inlet. An engine case may be coupled to the fan case via a vane extending between the fan case and the engine case. A strut apparatus may extend from the fan case and limit deflection of the fan case. The strut apparatus may comprise a first end proximate the fan case, and a second end coupled to at least one of the engine case or a structure for mounting the turbofan engine to an aircraft.

公开(公告)号：US20190017445A1

公开(公告)日：2019-01-17

申请号：US16025022

申请日：2018-07-02

Applicant: United Technologies Corporation

Inventor： Paul R. Adams ,  Shankar S. Magge ,  Joseph B. Staubach ,  Wesley K. Lord ,  Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: F02C7/36 ,  F02K3/06 ,  F02C9/18 ,  F01D11/12 ,  F01D5/06 ,  F01D25/24 ,  F02C3/04 ,  F02C7/20 ,  F04D19/02 ,  F02K3/075 ,  F02C3/107

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including an array of fan blades rotatable about an engine axis, a compressor including a first compressor section and a second compressor section, the second compressor section including a second compressor section inlet with a compressor inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, and a turbine having a first turbine section driving the first compressor section, a second turbine section driving the fan through an epicyclic gearbox, the second turbine section including blades and vanes, and wherein the second turbine section defines a maximum gas path radius and the fan blades define a maximum radius, and a ratio of the maximum gas path radius to the maximum radius of the fan blades is less than 0.6.

公开(公告)号：US10151247B2

公开(公告)日：2018-12-11

申请号：US15074829

申请日：2016-03-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/32 ,  F28D7/06 ,  F02K3/115 ,  F02C6/08 ,  F02C7/141 ,  F02C7/18 ,  F04D29/58 ,  F28F9/00 ,  F28F9/02 ,  F28D21/00

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：US10144519B2

公开(公告)日：2018-12-04

申请号：US14887932

申请日：2015-10-20

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Gabriel L. Suciu

IPC: B64D13/06 ,  F02C3/04 ,  F02K3/04 ,  F02K3/06 ,  F02C7/18 ,  F02C7/36 ,  F02K3/00 ,  F02C6/08 ,  F02C3/06 ,  F02C3/107 ,  F02C7/12 ,  F02C9/18

Abstract: A gas turbine engine includes a fan, a compressor section having at least two sequential compressors, a combustor section fluidly connected to the compressor section, and a turbine section fluidly connected to the combustor section. The turbine section includes at least a first turbine, a second turbine and a third turbine. One of the first turbine, the second turbine and the third turbine is a fan-drive turbine. An environmental control system air supply includes at least a first compressor bleed and a second compressor bleed. Each of the first compressor bleed and the second compressor bleed are positioned upstream of a highest pressure compressor of the at least two compressors.