公开(公告)号：US11168616B2

公开(公告)日：2021-11-09

申请号：US15980870

申请日：2018-05-16

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Christopher J. Hanlon ,  William G Sheridan

IPC: F02C7/36 ,  F02C6/00 ,  F02C9/00 ,  F02K3/06 ,  F16H1/28 ,  H02K7/116 ,  H02K7/14 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes among other possible things, a fan section including a plurality of fan blades, a first electric motor assembly that provides a first drive input for driving the fan blades about an axis, a turbine section, and a geared architecture driven by the turbine section and coupled to the fan section to provide a second drive input for driving the fan blades, and second electric motor assembly is coupled to rotate the geared architecture relative to a fixed structure controls a speed of the fan blades provided by a combination of the first drive input and the second drive input.

公开(公告)号：US20210231081A1

公开(公告)日：2021-07-29

申请号：US16752020

申请日：2020-01-24

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02K3/06 ,  F02C3/04

Abstract: A hybrid electric gas turbine engine includes a fan section having a fan, a turbine section having a turbine drivably connected to the fan through a main shaft that extends along a central longitudinal axis, a gas generating core extending along a first axis that is radially offset from the central longitudinal axis, a first electric motor drivably connected to the main shaft, wherein the electric motor is colinear with the main shaft, and an electric compressor extending along a second axis that is radially offset from the central longitudinal axis, the electric compressor in fluid communication with the second turbine section.

公开(公告)号：US10914235B2

公开(公告)日：2021-02-09

申请号：US16017042

申请日：2018-06-25

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Paul R. Hanrahan

IPC: F02C7/18 ,  F02C6/08 ,  F02C7/143 ,  F02C9/18

Abstract: A gas turbine engine includes a compressor section, a combustor fluidly connected to the compressor section via a primary flowpath and a turbine section fluidly connected to the combustor via the primary flowpath. Also included is a cascading cooling system having a first inlet connected to a first compressor bleed, a second inlet connected to a second compressor bleed downstream of the first compressor bleed, and a third inlet connected to a third compressor bleed downstream of the second compressor bleed. The cascading cooling system includes at least one heat exchanger configured to incrementally generate cooling air for at least one of an aft compressor stage and a foremost turbine stage relative to fluid flow through the turbine section.

公开(公告)号：US20200102849A1

公开(公告)日：2020-04-02

申请号：US16148442

申请日：2018-10-01

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Sean Danby

IPC: F01D17/16 ,  F01D9/04 ,  F01D15/10 ,  H02K7/18

Abstract: A gas turbine engine includes a turbine section that is configured to drive a fan through a fan shaft. The fan includes a plurality of fan blades rotatable about an axis of rotation of the gas turbine engine. A fan nacelle includes a first electrical machine component. The fan is located within the fan nacelle. A plurality of fan inlet guide vanes includes a second electrical machine component. The plurality of fan inlet guide vanes are rotatable about the axis.

公开(公告)号：US20200063657A1

公开(公告)日：2020-02-27

申请号：US16550576

申请日：2019-08-26

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Dmitriy B. Sidelkovskiy ,  Neil Terwilliger ,  William G. Sheridan

IPC: F02C3/067 ,  F02K3/06 ,  F02C7/32 ,  F02K3/072

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other possible things, a fan including a plurality of fan blades rotatable about an axis, a plurality of inlet guide vanes mounted forward of the plurality of fan blades, the plurality of inlet guide vanes selectively rotatable about the axis independent of the plurality of fan blades; and a motor for controlling rotation of the plurality of inlet guide vanes about the axis.

公开(公告)号：US20200025069A1

公开(公告)日：2020-01-23

申请号：US16291241

申请日：2019-03-04

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz

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

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan section including a fan having a plurality of fan blades, and a nacelle surrounding the plurality of fan blades, a compressor section including a low pressure compressor and a high pressure compressor, the low pressure compressor including a plurality of stages, and the high pressure compressor including 6 or more stages. A turbine section includes a fan drive turbine that drives the fan section through a gear arrangement, and including a second turbine that drives the high pressure compressor. A power ratio is provided by the combination of a first power input of the low pressure compressor and a second power input of the high pressure compressor, the power ratio defined by the second power input divided by the first power input, and the power ratio is less than or equal to 1.0

公开(公告)号：US20190383165A1

公开(公告)日：2019-12-19

申请号：US16012331

申请日：2018-06-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： Daniel Bernard Kupratis

IPC: F01D25/12 ,  F01D9/04 ,  F02C6/00

Abstract: An airfoil cooling system may include an airfoil that defines a first cooling chamber and a second cooling chamber. The first cooling chamber may be configured to receive a first cooling airflow from a first fluid source and the second cooling chamber may be configured to receive a second cooling airflow from a second fluid source that is different from the first fluid source. The airfoil may be a vane of a gas turbine engine. For example, the vane may be a first vane of a plurality of vanes of a turbine section of the gas turbine engine. The first cooling chamber may be a leading edge chamber of the first vane and the second cooling chamber may be an aft chamber of the first vane that is positioned aft of the leading edge chamber.

公开(公告)号：US20190383157A1

公开(公告)日：2019-12-19

申请号：US16012059

申请日：2018-06-19

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Frederick M. Schwarz ,  William G. Sheridan

IPC: F01D15/10 ,  F02C7/36 ,  F02K3/06 ,  H02K11/00 ,  H02K7/18

Abstract: A gas turbine engine according to an exemplary embodiment of this disclosure includes, among other things, a fan driven by a fan shaft rotatable about an engine axis; a fan drive electric motor providing a supplemental drive input to the fan; a turbine section driving an input shaft; a geared architecture driven by the input shaft of the turbine section and coupled to the fan shaft to provide a main drive input for driving the fan; and a generator including a rotor supported on the input shaft and a stator disposed on a static structure relative to the rotor, wherein the generator communicates electric power to power the fan drive electric motor.

公开(公告)号：US10364749B2

公开(公告)日：2019-07-30

申请号：US14974779

申请日：2015-12-18

Applicant: United Technologies Corporation

Inventor： Paul R. Hanrahan ,  Daniel Bernard Kupratis

IPC: F02C7/18 ,  F02C7/141 ,  F02C3/10 ,  F02K3/06 ,  F01D25/16 ,  F02C6/08 ,  F02C7/12

Abstract: A heat exchanger for a gas turbine engine includes a cooling air scoop that has a leading edge nose that is positioned adjacent to a downstream-most stator cascade of a fan section of the gas turbine engine. The cooling air scoop subtends only a sector of a circumference of the gas turbine engine. The heat exchanger also includes a cold side that is connected to the cooling air scoop and a hot side that is connected to a compressor section of the gas turbine engine.

公开(公告)号：US10364041B2

公开(公告)日：2019-07-30

申请号：US15218915

申请日：2016-07-25

Applicant: United Technologies Corporation

Inventor： Daniel Bernard Kupratis ,  Arthur W. Utay ,  Tania Bhatia Kashyap ,  Thomas N. Slavens ,  Kevin L. Rugg ,  Mark F. Zelesky ,  Brian D. Merry ,  Gabriel L. Suciu

IPC: B64D41/00 ,  F04D17/10 ,  F02C3/08 ,  F02C3/14

Abstract: An auxiliary power unit may comprise a twin centrifugal compressor including a first blade. A turbine may be disposed aft of the twin centrifugal compressor. The turbine may include a second blade. The first blade comprises a first material and the second blade comprises a second material. The first material may the same as the second material. The twin centrifugal compressor may include forward centrifugal compressor and an aft centrifugal compressor disposed aft of the forward centrifugal compressor.