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公开(公告)号：US11629646B2
公开(公告)日：2023-04-18
申请号：US16145431
申请日：2018-09-28
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Michael M. Romero
Abstract: A disclosed drive assembly for an auxiliary power unit includes a first drive shaft driven by an auxiliary power unit, a second drive shaft driven by a first electric motor, a differential gear system including a ring gear driven by the second drive shaft, a and planet gears supported within a carrier attached to the ring gear. The first drive shaft and an output shaft are coupled to the planet gears and a generator is driven by the output shaft. The electric motor and the auxiliary power unit combine to drive the output shaft.
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公开(公告)号：US11421590B2
公开(公告)日：2022-08-23
申请号：US16656931
申请日：2019-10-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan , Arthur M. Salve, Jr.
Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.
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公开(公告)号：US11415044B2
公开(公告)日：2022-08-16
申请号：US16431271
申请日：2019-06-04
Applicant: United Technologies Corporation
Inventor： Daniel Bernard Kupratis , Neil Terwilliger , Christopher J. Hanlon
Abstract: An aircraft gas turbine engine system comprises first and second gas turbine engines. The first gas turbine engine has first and second spools. A first power linkage connects the second gas turbine engine to the first spool of the gas turbine engine, and a second power linkage connects the second gas turbine engine to the second spool of the first gas turbine engine.
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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
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.
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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
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.
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Patent Agency Ranking
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
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.
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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
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.
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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
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.
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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
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
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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
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.
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