公开(公告)号：US10443543B2

公开(公告)日：2019-10-15

申请号：US15343470

申请日：2016-11-04

Applicant: United Technologies Corporation

Inventor： John P. Virtue, Jr. ,  Rishon Saftler ,  Frederick M. Schwarz

IPC: F01D19/02 ,  F02K3/068 ,  F02K3/075 ,  F04D29/64 ,  F01D11/18 ,  F02K3/02 ,  F02K3/06 ,  F01D19/00 ,  F01D25/16 ,  F01D25/36 ,  F02C7/26 ,  F02C7/32 ,  F02C9/42 ,  F02K3/11 ,  B64D27/00

Abstract: An aspect includes a system including a high compressor of a gas turbine engine having a ratio of a cold-rotor build clearance to a span between 0.7% and 7%. The cold-rotor build clearance is defined for a plurality of rotor blades of the high compressor with respect to an engine casing assembly interior surface of the high compressor, and the span is defined as a gap between a rotor disk of the high compressor and the engine casing assembly interior surface of the high compressor for at least a last two stages of the high compressor closest to a combustor section of the gas turbine engine. The system also includes at least two bowed rotor management systems for the gas turbine engine to prevent damage to the rotor blades for a bowed rotor condition of the high compressor under a plurality of operating conditions.

公开(公告)号：US10436120B2

公开(公告)日：2019-10-08

申请号：US13792303

申请日：2013-03-11

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Robert E. Malecki

IPC: F02K3/06 ,  F02C7/36 ,  F02C3/10 ,  F02K3/068 ,  B64D33/02 ,  F02C3/107

Abstract: A propulsion system includes a fan, a gear, a turbine configured to drive the gear to, in turn, drive the fan. The turbine has an exit point, and a diameter (Dt) is defined at the exit point. A nacelle surrounds a core engine housing. The fan is configured to deliver air into a bypass duct defined between the nacelle and the core engine housing. A core engine exhaust nozzle is provided downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance from the exit point. A ratio of the distance to the diameter is greater than or equal to about 0.90.

公开(公告)号：US20190291877A1

公开(公告)日：2019-09-26

申请号：US16360280

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael Winter ,  Charles E. Lents ,  Nathan Snape ,  Alan H. Epstein

IPC: B64D13/08 ,  F02C7/16 ,  F02C7/141

Abstract: A cryogenic cooling system for an aircraft includes a first air cycle machine, a second air cycle machine, and a means for collecting liquid air. The first air cycle machine is operable to output a cooling air stream based on a first air source. The second air cycle machine is operable to output a chilled air stream at a cryogenic temperature based on a second air source cooled by the cooling air stream of the first air cycle machine. An output of the second air cycle machine is provided to the means for collecting liquid air.

公开(公告)号：US10378359B2

公开(公告)日：2019-08-13

申请号：US15156367

申请日：2016-05-17

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： John W. Golan ,  Frederick M. Schwarz

IPC: F01D25/12 ,  F01D5/08 ,  B23P15/26 ,  F01D5/02 ,  F01D25/24 ,  F04D19/00 ,  F28D7/16 ,  F28F1/04 ,  F28F13/08 ,  F02C7/18 ,  F28F7/02 ,  F28D21/00

Abstract: A heat exchanger has a first plurality of passages extending in a first direction and to receive a first fluid and a second plurality of passages extending in a second direction, and to receive a second fluid, and the first plurality of passages being formed across a cross-sectional face of the heat exchanger, and there being distinct combined flow cross-sectional areas of the first plurality of passages in different locations across the cross-sectional face of the heat exchanger. A gas turbine engine and a method of forming a heat exchanger are also disclosed.

公开(公告)号：US10371061B2

公开(公告)日：2019-08-06

申请号：US15292405

申请日：2016-10-13

Applicant: United Technologies Corporation

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

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

Abstract: A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

公开(公告)号：US20190153941A1

公开(公告)日：2019-05-23

申请号：US16259250

申请日：2019-01-28

Applicant: United Technologies Corporation

Inventor： Pedro David Laureano ,  Frederick M. Schwarz

IPC: F02C3/10 ,  F02C3/107 ,  F02C7/06 ,  F01D5/02 ,  F02C7/36 ,  F04D29/054 ,  F01D21/04

Abstract: A disclosed gas turbine engine includes a compressor section including a first compressor disposed axially forward of a second compressor, a combustor in fluid communication with the compressor section and a turbine section in fluid communication with the combustor. The turbine section includes a first turbine driving the first compressor and a second turbine driving the second compressor. An inner shaft defines a driving link between the second compressor and the second turbine and an outer shaft defines a driving link between the first compressor and the first turbine. The inner shaft and the outer shaft are concentric about a common axis of rotation. A bumper is disposed on the inner shaft within an axial region common to an aft portion of the outer shaft for accommodating interaction between the inner and outer shafts during high load conditions.

公开(公告)号：US20190153887A1

公开(公告)日：2019-05-23

申请号：US16173051

申请日：2018-10-29

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan ,  Michael E. McCune ,  Gabriel L. Suciu

IPC: F01D15/12 ,  F02C7/36 ,  F16H57/04 ,  F01D25/18 ,  F16H1/28 ,  F02K3/06

CPC classification number: F01D15/12 ,  F01D25/18 ,  F02C7/36 ,  F02K3/06 ,  F05D2220/36 ,  F05D2240/50 ,  F05D2260/40311 ,  F05D2260/98 ,  F16H1/28 ,  F16H57/0479 ,  F16H57/0486

Abstract: A turbofan engine assembly includes a nacelle and a turbofan engine. The turbofan engine includes a fan, which includes a fan rotor having fan blades, and a nacelle enclosing the fan rotor and the blades. A turbine rotor drives the fan rotor. An epicyclic gear reduction is positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and four intermediate gears that engage the sun gear and the ring gear. A gear ratio of the gear reduction is greater than 3.06. The fan drive turbine drives the sun gear to, in turn, drive the fan rotor.

公开(公告)号：US10280794B2

公开(公告)日：2019-05-07

申请号：US14769392

申请日：2013-12-18

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Lisa I. Brilliant

IPC: F01D25/14 ,  F02C7/24 ,  F02C7/36 ,  F01D5/02 ,  F01D5/12 ,  F01D9/04 ,  F01D25/24 ,  F02C3/04 ,  F01D5/08 ,  F01D25/26 ,  F02C7/14

Abstract: A gas turbine engine having an engine axis and method of manufacturing the same is disclosed. The gas turbine engine may comprise a fan configured to drive air, a low pressure compressor section having a core flow path and configured to draw in and compress air flowing along the core flow path, a spool configured to drive the fan, and geared architecture configured to adjust the fan speed. The gas turbine engine may also include a housing defining a compartment that encloses the geared architecture. The housing is disposed between the core flow path and the axis, and includes a shielded mid-section that is in thermal communication with the core flow path of the low pressure compressor section. The shielded mid-section includes an outer layer and an insulator adjacent to the outer layer.

公开(公告)号：US10280757B2

公开(公告)日：2019-05-07

申请号：US15029802

申请日：2014-10-07

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F01D5/14 ,  F01D17/16 ,  F01D9/04 ,  F01D17/14 ,  F04D29/68 ,  F04D29/56

Abstract: A component for a gas turbine engine, according to an exemplary aspect of the present disclosure includes, among other things, an airfoil that includes a pressure side surface and a suction side surface that join together at a leading edge and a trailing edge and a flow channel that extends between the pressure side surface and the suction side surface.

公开(公告)号：US20190120084A1

公开(公告)日：2019-04-25

申请号：US16227271

申请日：2018-12-20

Applicant: United Technologies Corporation

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

IPC: F01D25/16 ,  F02K3/06 ,  F02C7/36 ,  F04D25/02 ,  F04D29/056 ,  F02C7/06 ,  F04D19/02 ,  F04D29/32 ,  F04D27/00 ,  F04D25/04 ,  F01D9/04 ,  F01D5/06 ,  F01D15/12 ,  F02C3/107 ,  F04D29/66 ,  F02C7/20

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan, and an outer housing surrounding the fan to define a bypass flow path, a compressor, a turbine section including a fan drive turbine and a second turbine, an epicyclic gear system with a gear reduction, the fan drive turbine driving the fan through the gear system, and the gear system straddle-mounted by first and second bearings. The fan drive turbine has a first exit area at a first exit point and is rotatable at a first speed. 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.