公开(公告)号：US20190145316A1

公开(公告)日：2019-05-16

申请号：US15809150

申请日：2017-11-10

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Neal R. Herring

IPC: F02C7/141 ,  F02C7/18 ,  F02K3/02 ,  F02K3/04

Abstract: A gas turbine engine includes a fan rotor, a compressor aft of the fan rotor, a combustor aft of the compressor, and a turbine section aft of the combustor, the turbine section configured to drive the compressor section and the fan rotor. A cooling air system includes an input connected to a compressed air tap, an output connected to at least the turbine section, and a heat exchanger having a first path and a second path. The first path is disposed between the input and the output. A valve and a propulsor are disposed along a lower pressure cooling air path. The heat exchanger second path is in fluid communication with at least a portion of the lower pressure cooling air path. The valve is configured to control flow within the heat exchanger second path. A cooling system and a method are also disclosed.

公开(公告)号：US10288010B2

公开(公告)日：2019-05-14

申请号：US15405498

申请日：2017-01-13

Applicant: United Technologies Corporation

Inventor： David P. Houston ,  Daniel Bernard Kupratis ,  Frederick M. Schwarz

IPC: F02K3/06 ,  F02K3/072 ,  F02C7/36 ,  F01D25/16 ,  F01D5/02 ,  F02C7/06 ,  F01D5/06 ,  F01D9/02 ,  F02C3/04 ,  F02C3/107 ,  F02C9/18 ,  F02K1/78 ,  F04D27/00 ,  F04D29/32 ,  F01D9/04

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：US10287982B2

公开(公告)日：2019-05-14

申请号：US14826905

申请日：2015-08-14

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F02K3/115 ,  F02C7/141 ,  F02C7/20 ,  F04D29/58 ,  F28D1/047 ,  F28D7/06 ,  F28D21/00 ,  F04D19/02 ,  F28F9/22

Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. The HEX may comprise a central manifold comprising an inlet portion, a first outlet portion, and a second outlet portion. The HEX may further comprise a plurality of tubes coupled to the central manifold, the plurality of tubes comprising at least a first tube, a second tube, a third tube, and a fourth tube, a shroud at least partially encasing said plurality of tubes, and a cooling air flow path defined by at least one of the shroud, the plurality of tubes, and an outer surface of the central manifold, wherein the cooling air flow path is orthogonal to said plurality of tubes.

公开(公告)号：US10253695B2

公开(公告)日：2019-04-09

申请号：US15062400

申请日：2016-03-07

Applicant: United Technologies Corporation

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F28F9/02 ,  F02K3/115 ,  F02C7/141 ,  F04D29/58 ,  F28F9/24 ,  F28D7/06 ,  F28D1/047 ,  F28D21/00

Abstract: A heat exchanger (HEX) for cooling air in a gas turbine engine is provided. An adjustable damper is provided. The adjustable damper may be for damping a movement of the HEX relative to the gas turbing engine. An adjustable damper may comprise: a first tube; a second tube located at least partially within the first tube; a housing coupled to the second tube; a moveable member, the moveable member comprising a contacting surface in contact with the second tube; an adjusting member adjustably coupled to the housing; and a spring member located between the moveable member and the adjusting member, the spring member configured to at least one of compress or decompress in response to adjusting member moving relative to the housing.

公开(公告)号：US20190048803A1

公开(公告)日：2019-02-14

申请号：US16025094

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

CPC classification number: F02C7/36 ,  F01D5/06 ,  F01D11/122 ,  F01D25/24 ,  F02C3/04 ,  F02C3/107 ,  F02C7/20 ,  F02C9/18 ,  F02K3/06 ,  F02K3/075 ,  F04D19/02 ,  F05B2250/283 ,  F05D2220/32 ,  F05D2220/323 ,  F05D2240/35 ,  F05D2240/60 ,  F05D2260/40311

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, 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：US20190039167A1

公开(公告)日：2019-02-07

申请号：US15666204

申请日：2017-08-01

Applicant: United Technologies Corporation

Inventor： Michael F. Machinchick ,  Frederick M. Schwarz

IPC: B23K20/12 ,  F04D29/32

Abstract: A method of making an integrally bladed rotor is disclosed. The method includes providing a rotor disk comprising a radially outer rim surface that includes a recessed area thereon. A blade having an airfoil and a base is positioned such that a base surface is in contact with the recessed area with a gap between the base surface and the recessed area at a perimeter of the recessed area. Heat, pressure, and motion between the blade and the rotor disk are applied to friction weld the base surface to the recessed area.

公开(公告)号：US20190017446A1

公开(公告)日：2019-01-17

申请号：US16025038

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 a circumferential array of fan blades, a compressor in fluid communication with the fan, the compressor including a first compressor section and a second compressor, the second compressor section including a second compressor section inlet with a second compressor section inlet annulus area, a fan duct including a fan duct annulus area outboard of the second compressor section inlet, a shaft assembly having a first portion and a second portion, a turbine in fluid communication with the combustor, the turbine having a first turbine section coupled to the first portion of the shaft assembly to drive the first compressor section, and a second turbine section coupled to the second portion of the shaft assembly to drive the fan, an epicyclic transmission coupled to the fan and rotatable by the second turbine section through the second portion of the shaft assembly to allow the second turbine to turn faster than the fan, wherein the second turbine section includes a maximum gas path radius and the fan blades include 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：US20190017410A1

公开(公告)日：2019-01-17

申请号：US16131095

申请日：2018-09-14

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D21/00 ,  F01D25/20 ,  F02C3/04 ,  F02C3/107 ,  F02C7/06 ,  F02K3/06 ,  F01D15/12 ,  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：US10174678B2

公开(公告)日：2019-01-08

申请号：US15042377

申请日：2016-02-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Amy R. Grace

IPC: F02C7/26 ,  F02C7/268 ,  F01D25/36 ,  F02C3/04 ,  F02C9/00 ,  F01D19/02 ,  G01H1/00

Abstract: A bowed rotor start mitigation system for a gas turbine engine is provided. The bow rotor start mitigation system includes a controller operable to receive a speed input indicative of a rotor speed of the gas turbine engine and a measured temperature of the gas turbine engine. The controller is further operable to drive motoring of the gas turbine engine by oscillating the rotor speed within a motoring band for a motoring time based on the measured temperature when a start sequence of the gas turbine engine is initiated.

公开(公告)号：US20180363489A1

公开(公告)日：2018-12-20

申请号：US16109842

申请日：2018-08-23

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz

IPC: F01D15/12 ,  F02C3/107 ,  F02K3/06 ,  F01D5/34 ,  F02C3/06 ,  F01D1/18 ,  F01D5/02

Abstract: A gas turbine comprises a compressor module, with a lower pressure compressor section including a plurality of stages, with at least one of the plurality of stages being an integrally bladed rotor. A higher pressure compressor section includes a plurality of stages with at least one of the plurality of stages being an integrally bladed rotor. A fan drive turbine shaft drives a fan rotor through a gear reduction. The fan rotor delivers a portion of air into a bypass duct, and a portion of air into the compressor module. A bypass ratio defined by the volume of air delivered into the bypass duct compared to the volume of air delivered into the compressor module is greater than or equal to about 6.0.