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公开(公告)号：US20210054782A1
公开(公告)日：2021-02-25
申请号：US16545281
申请日：2019-08-20
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Daniel Bernard Kupratis , Paul R. Hanrahan
Abstract: A gas turbine engine is disclosed. In various embodiments, the gas turbine engine includes a low speed spool; a first compressor, a turbine and a generator rotationally coupled via the low speed spool; a high speed spool; and a second compressor and a motor rotationally coupled via the high speed spool.
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公开(公告)号：US20180334961A1
公开(公告)日：2018-11-22
申请号：US15599149
申请日：2017-05-18
Applicant: United Technologies Corporation
Inventor： Paul R. Hanrahan , Jonathan Ortiz
CPC classification number: F02C7/18 , F01D5/081 , F01D9/02 , F02C3/04 , F02C6/08 , F02C7/185 , F02C9/18 , F02K3/06 , F05D2220/32 , F05D2240/24 , F05D2240/35 , F05D2260/213
Abstract: A cooling system for a component of a gas turbine engine includes a first airflow passage configured to direct a first airflow to a mixing chamber and a second airflow passage to configured direct a second airflow to the mixing chamber, the second airflow having a higher temperature than the first airflow, and a cooling airflow passage to direct a cooling airflow from the mixing chamber to the component, the cooling airflow comprising the first airflow and the second airflow. The airflow passages are configured and sized to allow an amount of cooling airflow for unrestricted engine operation. When the first airflow passage is disabled, the second airflow passage and cooling airflow passage are configured and sized to allow an amount of cooling airflow which is adequate to permit continued safe engine operation restricted to within only a portion of its normal parameters and operating envelope.
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公开(公告)号：US10100739B2
公开(公告)日：2018-10-16
申请号：US14714554
申请日：2015-05-18
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：US09945262B2
公开(公告)日：2018-04-17
申请号：US14625025
申请日：2015-02-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： Paul R. Hanrahan , George E. Allen , Christopher M. Juh
CPC classification number: F01D25/285 , F01D5/026 , F05D2230/60 , F05D2230/70
Abstract: A system for maintaining a position of a bearing compartment in a gas turbine during disassembly of a low-pressure turbine of the gas turbine engine includes a forward annular shaft defining an engine centerline axis. The system includes a ring radially inward from and engaged with an inner diameter surface of the forward annular shaft. An aft annular shaft is radially inward from the forward annular shaft and aft of the ring. The ring is connected to a forward end of the aft annular shaft for common rotation therewith. The ring retains the aft annular shaft during disassembly. The system includes a stack nut axially held between an aft facing shoulder of the forward annular stub shaft and a forward facing surface of the ring to retain the stack nut during disassembly.
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公开(公告)号：US11578668B2
公开(公告)日：2023-02-14
申请号：US15608293
申请日：2017-05-30
Applicant: United Technologies Corporation
Inventor： Jonathan Ortiz , Taryn Narrow , John H. Mosley , Zachary Mott , Paul R. Hanrahan
Abstract: A gas turbine engine includes a compressor section, a combustor, and a turbine section. The turbine section includes a high pressure turbine comprising a plurality of turbine blades. The gas turbine engine includes a tap for tapping air that is compressed by the compressor, to be passed through a heat exchanger to cool the air, the cooled air to be passed to the plurality of turbine blades. A sensor is located downstream of a leading edge of the combustor, and is configured to measure a characteristic of the cooled air. A controller is configured to compare the measured characteristic to a threshold and control an operating condition of the gas turbine engine based on the comparison.
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Patent Agency Ranking
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：US11268444B2
公开(公告)日：2022-03-08
申请号：US15599149
申请日：2017-05-18
Applicant: United Technologies Corporation
Inventor： Paul R. Hanrahan , Jonathan Ortiz
Abstract: A cooling system for a component of a gas turbine engine includes a first airflow passage configured to direct a first airflow to a mixing chamber and a second airflow passage to configured direct a second airflow to the mixing chamber, the second airflow having a higher temperature than the first airflow, and a cooling airflow passage to direct a cooling airflow from the mixing chamber to the component, the cooling airflow comprising the first airflow and the second airflow. The airflow passages are configured and sized to allow an amount of cooling airflow for unrestricted engine operation. When the first airflow passage is disabled, the second airflow passage and cooling airflow passage are configured and sized to allow an amount of cooling airflow which is adequate to permit continued safe engine operation restricted to within only a portion of its normal parameters and operating envelope.
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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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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：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
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.
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