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公开(公告)号：US11480111B2
公开(公告)日：2022-10-25
申请号：US16412771
申请日：2019-05-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David K. Jan , Dietmar Giebert , Thomas G. Cunningham, Jr.
Abstract: A gas turbine engine with a compressor supplying compressed air. A combustor receives the compressed air and fuel and generates a flow of combusted gas. A turbine receives a core flow of the combusted gas to rotate a turbine rotor. A turbine inlet nozzle directs the combusted gas to the turbine rotor. Vanes are disposed in the turbine inlet nozzle and rotate to vary a flow area through which the core flow passes. The vanes adjust a pressure ratio of the gas turbine engine to compensate for changing operational requirements of the gas turbine engine by rotating to positions matching the changing operational requirements.
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公开(公告)号：US20200095930A1
公开(公告)日：2020-03-26
申请号：US16137102
申请日：2018-09-20
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Eric Blumer , David K. Jan
Abstract: A variable gear ratio gas turbine engine system includes a planetary gear set, a gas turbine engine, an electric machine, and a controller. The gas turbine engine includes at least a low-pressure compressor, a high-pressure compressor, a combustor, a high-pressure turbine, and a low-pressure turbine. The low-pressure turbine is coupled to the low-pressure compressor via the planetary gear set. The electric machine is coupled to the planetary gear set and its rotational speed is used, at least in part, to vary the gear ratio of the planetary gear set. The controller is in operable communication with the gas turbine engine and the electric machine and is configured to control: the low-pressure turbine to rotate at a substantially constant speed and the rotational speed of the electric machine to thereby vary the gear ratio of the planetary gear set, whereby the speed at which the low-pressure compressor rotates is also varied.
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3.发明申请AUXILIARY POWER UNITS (APUs) AND METHODS AND SYSTEMS FOR ACTIVATION AND DEACTIVATION OF A LOAD COMPRESSOR THEREIN 有权辅助动力单元（APU）及其负载压缩机的启动和停止的方法和系统公开(公告)号：US20140241906A1
公开(公告)日：2014-08-28
申请号：US13781239
申请日：2013-02-28
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David K. Jan , Christopher Zollars
IPC: F04D25/02
CPC classification number: F04D17/10 , F01D15/08 , F02C6/08 , F02C9/18 , F04D25/022 , F04D27/0292 , F05D2220/50
Abstract: Auxiliary power units and methods and systems for activation and deactivation of a load compressor therein are provided. Auxiliary power unit includes the load compressor having an impeller, APU engine, coupling member, pre-spinning means, and APU controller. APU engine is adapted to be mechanically engaged to load compressor to drive load compressor to provide pneumatic power and to be disengaged when the need for pneumatic power ceases. Coupling member couples load compressor and APU engine and is configured to be controllably moved between an engaged position in which the APU engine is mechanically engaged with the load compressor, and a disengaged position, in which the APU engine is disengaged from the load compressor. APU controller is operably coupled to load compressor, APU engine, coupling member, and pre-spinning means and adapted to receive and be responsive to rotational speed signals for controlling movement of coupling member between engaged and disengaged positions.
Abstract translation: 提供了用于在其中启动和停用负载压缩机的辅助动力装置和方法和系统。 辅助动力单元包括具有叶轮，APU发动机，联接构件，预纺装置和APU控制器的负载压缩机。 APU发动机适于机械接合以加载压缩机以驱动负载压缩机以提供气动动力并且当需要气动动力停止时被分离。 耦合构件对负载压缩机和APU发动机，并且构造成在APU发动机与负载压缩机机械接合的接合位置和APU发动机从负载压缩机脱离的分离位置之间可控地移动。 APU控制器可操作地耦合到负载压缩机，APU发动机，联接构件和预纺装置，并适于接收和响应于转速信号，以控制联接构件在接合位置和脱离位置之间的移动。
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公开(公告)号：US20180195729A1
公开(公告)日：2018-07-12
申请号：US15403286
申请日：2017-01-11
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K. Jan , Mark Matwey
CPC classification number: F23R3/425 , F01D9/023 , F01D9/026 , F01D11/08 , F01D25/12 , F02C3/04 , F02C7/18 , F05D2220/32 , F05D2220/50 , F05D2240/35 , F05D2260/205 , F05D2260/22141 , F23R3/26 , Y02T50/675
Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
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公开(公告)号：US20170304929A1
公开(公告)日：2017-10-26
申请号：US15648577
申请日：2017-07-13
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Amandine Miner , David K. Jan , Don Mittendorf , Jason Smoke
IPC: B23K20/02 , B23K1/00 , F01D5/30 , B23K20/22 , B23K20/26 , B23P15/00 , F01D5/34 , B23K20/14 , B23K31/02 , B23K101/00 , B23K20/00
CPC classification number: B23K20/028 , B23K1/00 , B23K1/0018 , B23K20/002 , B23K20/021 , B23K20/023 , B23K20/14 , B23K20/22 , B23K20/26 , B23K31/02 , B23K2101/001 , B23P15/006 , F01D5/3061 , F01D5/34 , F05D2220/323 , F05D2230/236 , F05D2230/60 , F05D2300/17 , F05D2300/606 , F05D2300/607 , Y10T29/49323
Abstract: Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.
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Patent Agency Ranking
公开(公告)号：US20170254209A1
公开(公告)日：2017-09-07
申请号：US15062952
申请日：2016-03-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K. Jan , Amandine Miner , Deanna Pinar Chase , Michael Kahrs , Lorenzo Crosatti
CPC classification number: F01D5/187 , F01D1/08 , F01D5/045 , F01D5/046 , F01D5/3061 , F05D2220/32 , F05D2260/202 , Y02T50/673 , Y02T50/676
Abstract: A turbine blade and a radial turbine having at least one blade is provided. The turbine blade includes a trailing edge and a leading edge opposite the trailing edge. The turbine blade also includes a cooling passage defined internally within the turbine blade. The cooling passage is in fluid communication with a source of cooling fluid via a single inlet to receive a cooling fluid. The cooling passage diverges at a first point downstream from the single inlet into at least two branches that extend along the at least one blade from the first point to a second point near a tip of the leading edge and the cooling passage converges at the second point.
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公开(公告)号：US20170096911A1
公开(公告)日：2017-04-06
申请号：US14873853
申请日：2015-10-02
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Ed Zurmehly , David R. Waldman , Deanna Pinar Chase , David K. Jan , Greg Ockenfels , Alonso Peralta-Duran
CPC classification number: F01D25/246 , F01D9/02 , F01D11/005 , F05D2220/32 , F05D2230/60 , F05D2240/11
Abstract: Compliant coupling systems and methods are provided for coupling a shroud to an engine casing. The complaint coupling system includes a retaining ring adapted to be positioned adjacent to the shroud and adapted to be coupled to the engine casing. The retaining ring defines a coupling channel about a circumference of the retaining ring and at least one notch that interrupts the coupling channel. The complaint coupling system also includes a first clip received within the coupling channel. The first clip has a biasing portion that extends into a space defined by the at least one notch, and the biasing portion is adapted to contact the shroud. The complaint coupling system includes a second clip received within the coupling channel. The second clip has a bumper portion that extends into the spaced defined by the at least one notch, and the bumper portion is adapted to contact the shroud
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公开(公告)号：US20140348664A1
公开(公告)日：2014-11-27
申请号：US13892828
申请日：2013-05-13
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David K. Jan , Amandine Miner
IPC: F01D5/08
CPC classification number: F01D5/081 , F01D5/045 , F01D5/046 , F01D5/087 , F01D5/187 , F01D5/3061 , F05D2240/81 , F05D2260/201 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: An integral turbine includes a forward hub section and an aft hub section. The forward hub section and the aft hub section are metallurgically coupled to one another along an annular interface that resides within a plane generally orthogonal to a rotational axis of the axially-split turbine. The turbine further includes an airfoil blade ring metallurgically coupled to a radial outer surface of the coupled forward and aft hub sections and an impingement cavity formed within an interior portion of the coupled forward and aft hub sections. The impingement cavity includes an interior surface that is positioned proximate to the radial outer surface of the coupled forward and aft hub sections. Further, an impingement cooling air flow impinges against the interior surface of the impingement cavity to provide convective and conductive cooling to the radial outer surface of the coupled forward and aft hub sections.
Abstract translation: 整体涡轮机包括前轮毂部分和后轮毂部分。 前轮毂部分和后轮毂部分沿着环形接口彼此冶金地联接，该环形接口位于大致垂直于轴向分离的涡轮机的旋转轴线的平面内。 涡轮进一步包括翼形叶片环，该叶片环冶金地联接到所耦合的前和后轮毂部分的径向外表面，以及形成在所耦合的前部和后部毂部分的内部部分内的冲击腔。 冲击腔包括内接表面，该内表面靠近所耦合的前后轮毂段的径向外表面。 此外，冲击冷却空气流撞击冲击腔的内表面，以向耦合的前和后毂部分的径向外表面提供对流和导电冷却。
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公开(公告)号：US11293292B2
公开(公告)日：2022-04-05
申请号：US16736199
申请日：2020-01-07
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K. Jan , Mark Matwey
Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
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公开(公告)号：US10655859B2
公开(公告)日：2020-05-19
申请号：US15403286
申请日：2017-01-11
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K. Jan , Mark Matwey
Abstract: A gas turbine engine includes a compressor section and a combustion section with a scroll, a scroll baffle, a combustor, and a combustor case. The scroll defines an interior scroll flow path. The scroll baffle surrounds the scroll to define a scroll cooling passage. The combustor case surrounds the combustor and the scroll baffle to define a collector space. Moreover, the engine includes a turbine section with a turbine rotor and a turbine rotor blade shroud that includes a shroud cooling passage. The compressor flow path is fluidly connected to the scroll for cooling the scroll. Also, the scroll cooling passage is fluidly connected to the shroud cooling passage for cooling the turbine rotor blade shroud. Furthermore, the shroud cooling passage is fluidly connected to the collector space. Flow from the collector space flows into the combustor, along the interior scroll flow path, toward the turbine rotor.
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