公开(公告)号：US20200049077A1

公开(公告)日：2020-02-13

申请号：US16598048

申请日：2019-10-10

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Daniel Bernard Kupratis ,  Brian D. Merry ,  Gabriel L. Suciu ,  William K. Ackermann

IPC: F02C7/36 ,  F02K3/06 ,  F02C3/107 ,  F01D25/16 ,  F01D5/06 ,  F02C3/06 ,  F02C7/06 ,  F04D29/32

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. The high pressure turbine is supported by a bearing positioned at a point where the first shaft connects to a hub carrying turbine rotors associated with the second turbine section.

公开(公告)号：US10526916B2

公开(公告)日：2020-01-07

申请号：US15138727

申请日：2016-04-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Frederick M. Schwarz ,  Paul W. Duesler

IPC: F01D17/10 ,  F01D25/12 ,  F01D25/24 ,  F02C7/18 ,  F02K3/115 ,  F02K9/64 ,  F28D1/047 ,  F28D7/16 ,  F28F21/08 ,  F28F9/00 ,  F28F9/007 ,  F28F9/013 ,  F28F9/02 ,  F04D29/32 ,  F01D5/02

Abstract: A heat exchanger for use in a gas turbine engine has a central body including an inlet manifold and at least one tube providing an outlet manifold, and a plurality of tubes communicating holes in an outer periphery of the inlet manifold to holes in an outer periphery of the outlet manifold, and passages for cooling air to pass across the tubes. A gas turbine engine is also disclosed.

公开(公告)号：US10508562B2

公开(公告)日：2019-12-17

申请号：US14935673

申请日：2015-12-01

Applicant: UNITED TECHNOLOGIES CORPORATION

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

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

Abstract: A gas turbine engine has a fan rotor, a turbine rotor driving the fan rotor, and an epicyclic gear reduction positioned between the fan rotor and the turbine rotor. The epicyclic gear reduction includes a ring gear, a sun gear, and no more than four intermediate gears that engage the sun gear and the ring gear. The fan drive turbine is configured to drive the sun gear to, in turn, drive the ring gears to, in turn, drive the fan rotor.

公开(公告)号：US10472071B2

公开(公告)日：2019-11-12

申请号：US14737580

申请日：2015-06-12

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Stephen G. Pixton

IPC: B64D13/02 ,  F01D5/06 ,  F01D17/10 ,  B64D27/10 ,  F02K3/06 ,  F02C6/08 ,  F02C9/18

Abstract: A gas turbine engine comprises at least two compressor rotors, including a first lower pressure compressor rotor and a second higher pressure compressor rotor. At least two corresponding air taps include a low tap for tapping low pressure compressor air from a location downstream of a first stage of the lower pressure compressor rotor, and upstream of a first stage of the higher pressure compressor rotor, and a high tap to tap air downstream of the first stage of the higher pressure compressor rotor. an air handling system selectively communicates both the low tap and the high tap to an air use destination. Air is selectively supplied from the low tap to the air handling system at a high power operation and from the high tap to the air handling system at a low power operation.

公开(公告)号：US20190323430A1

公开(公告)日：2019-10-24

申请号：US15956884

申请日：2018-04-19

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael G. McCaffrey

IPC: F02C7/18 ,  F01D25/12 ,  F01D5/18 ,  F01D5/08

Abstract: A method of modulating cooling of gas turbine engine components includes the steps of identifying an input indicative of a usage rate for at least a first gas turbine engine component of a plurality of gas turbine engine components. A cooling system is operated for at least the first gas turbine engine component. The cooling system is moved between a higher cooling potential mode and a lower cooling potential mode based on the identified rate. A gas turbine engine is also disclosed.

公开(公告)号：US10443612B2

公开(公告)日：2019-10-15

申请号：US15102155

申请日：2014-12-16

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  Michael A. Weisse

IPC: F04D29/38 ,  F01D5/18 ,  B23K20/12 ,  F02C3/04 ,  F04D29/32 ,  F01D5/14 ,  B23K101/00

Abstract: An airfoil for a turbine engine includes an airfoil body with a cover mounting support, a first cover, and a second cover. The airfoil body includes a solid perimeter portion surrounding a recess formed into at least one of a suction side and a pressure side of the airfoil body, while the cover mounting support extends through the recess. The first cover can be engaged with a first edge of the recess and joined to a first portion of the cover mounting support by a first stir weld. The second cover can be engaged with a second edge of the recess, and joined to a second portion of the cover mounting support by a second stir weld.

公开(公告)号：US20190218974A1

公开(公告)日：2019-07-18

申请号：US16364524

申请日：2019-03-26

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Paul W. Duesler ,  Frederick M. Schwarz

IPC: F02C7/18 ,  F02C7/141 ,  F02C7/20 ,  F04D29/58 ,  F28D7/06 ,  F02K3/115 ,  F28D1/047

CPC classification number: F02C7/185 ,  F02C7/141 ,  F02C7/18 ,  F02C7/20 ,  F02K3/115 ,  F04D19/02 ,  F04D29/5826 ,  F05D2260/213 ,  F28D1/0475 ,  F28D7/06 ,  F28D2021/0026 ,  F28F2009/222 ,  F28F2245/00 ,  F28F2250/06 ,  F28F2255/00 ,  Y02T50/675

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：US20190218973A1

公开(公告)日：2019-07-18

申请号：US16360329

申请日：2019-03-21

Applicant: United Technologies Corporation

Inventor： Frederick M. Schwarz ,  John T. Schmitz

IPC: F02C7/18 ,  F02K3/105 ,  F02C7/32 ,  F02C7/12 ,  F02K3/115 ,  F02K3/077 ,  B64D33/10 ,  F01D25/14 ,  F02C7/14 ,  F01D25/08 ,  B64D33/08 ,  B64D33/12

CPC classification number: F02C7/185 ,  B64D33/08 ,  B64D33/10 ,  B64D33/12 ,  B64D2033/024 ,  F01D25/08 ,  F01D25/14 ,  F02C7/12 ,  F02C7/14 ,  F02C7/32 ,  F02K3/077 ,  F02K3/105 ,  F02K3/115 ,  F05D2260/20 ,  F05D2260/213 ,  F28D2021/0021 ,  F28D2021/0026 ,  Y02T50/675

Abstract: A heat exchange module is provided for a turbine engine. The heat exchange module includes a duct and a plurality of heat exchangers. The duct includes a flowpath defined radially between a plurality of concentric duct walls. The flowpath extends along an axial centerline through the duct between a first duct end and a second duct end. The heat exchangers are located within the flowpath, and arranged circumferentially around the centerline.

公开(公告)号：US20190162121A1

公开(公告)日：2019-05-30

申请号：US15823639

申请日：2017-11-28

Applicant: United Technologies Corporation

Inventor： Joseph Brent Staubach ,  Nathan Snape ,  Frederick M. Schwarz ,  Charles E. Lents ,  Michael K. Ikeda

IPC: F02C9/18 ,  F02C7/18 ,  B64D33/02 ,  B64D13/00

Abstract: A lower pressure tap is connected to a first heat exchanger to be cooled by cooling air, and then to a selection valve. The selection valve selectively delivers the lower pressure tap air to a boost compressor. The lower pressure tap air downstream of the boost compressor is connected to cool the at least one turbine. The selection valve also selectively delivers a portion of the lower pressure tap air across a first cooling turbine, and to a line associated with an air delivery system for a cabin on an associated aircraft. A portion of the air downstream of the first cooling turbine is connected to a second cooling turbine, and air downstream of the second cooling turbine is connected for use in a cold loop A method of operating an air supply system is also disclosed.

公开(公告)号：US10294871B2

公开(公告)日：2019-05-21

申请号：US14875750

申请日：2015-10-06

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 according to an example of the present disclosure includes, among other things, a geared architecture configured to drive a fan section including a fan, and a turbine section configured to drive the geared architecture. The turbine section has an exit point, and a diameter (Dt) defined as the outer diameter of a last blade airfoil stage in the turbine section 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 downstream of the exit point. A downstream most point of the core engine exhaust nozzle is defined at a distance (Lc or Ln) from the exit point.