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1.发明公开公开(公告)号：US20230340910A1
公开(公告)日：2023-10-26
申请号：US18216954
申请日：2023-06-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： James Robert JARVO , Cedric SAINTIGNAN , Joseph Daniel Maxim CIRTWILL , Kian MCCALDON , Marc-Andre TREMBLAY , David WADDLETON
IPC: F02C7/30 , F02C7/236 , F02C7/232 , F02C7/22 , F02C9/32 , F02C9/42 , F02C7/228 , F02C6/00 , F02C6/16
CPC classification number: F02C7/30 , F02C6/00 , F02C6/16 , F02C7/222 , F02C7/228 , F02C7/232 , F02C7/236 , F02C9/32 , F02C9/42
Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
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公开(公告)号：US20200300179A1
公开(公告)日：2020-09-24
申请号：US16361819
申请日：2019-03-22
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David WADDLETON , Benjamin RENAUD , Sebastien BERGERON , Etienne PLAMONDON , Jean-Gabriel GAUVREAU
Abstract: A rotodynamic pump for pumping a fluid includes an impeller, a housing surrounding the impeller, and a pressure regulating mechanism. The pressure regulating mechanism is configured to adjust the clearance between the impeller and the impeller housing to regulate pressure of the fluid downstream of the impeller. A method of regulating the delivery pressure is also disclosed.
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公开(公告)号：US20220178306A1
公开(公告)日：2022-06-09
申请号：US17116410
申请日：2020-12-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sean DURAND , Harris SHAFIQUE , David WADDLETON
Abstract: The fuel system can have a jet fuel subsystem having a jet fuel conduit extending from a first reservoir area to a fuel nozzle across an auxiliary system operable using a flow of the jet fuel, at least one fuel delivery system operable to circulate a controlled flow rate of the jet fuel within said conduit and across the auxiliary system, a recirculation conduit branching off from the jet fuel conduit downstream of the auxiliary system, an actuator valve operable to selectively direct a flow of jet fuel to the at least one fuel nozzle or to the recirculation conduit; and an alternative fuel subsystem having an alternative fuel conduit extending from a second reservoir area to a fuel nozzle.
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公开(公告)号：US20200331623A1
公开(公告)日：2020-10-22
申请号：US16704281
申请日：2019-12-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David WADDLETON
Abstract: An aircraft motive flow line includes an outer tube made out of a first material and an inner tube extending longitudinally inside the outer tube. The inner tube is made out of a second material having a thermal conductivity coefficient lower than that of the first material. The first material has a strength coefficient greater than that of the second material. The inner tube is sized and held in position relative to the outer tube so as to define a gap between an exterior of the inner tube and an interior of the outer tube. A port fluidly connects an interior of the inner tube to the gap.
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公开(公告)号：US20140252171A1
公开(公告)日：2014-09-11
申请号：US13790653
申请日：2013-03-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Kevin Allan DOOLEY , David WADDLETON , Thomas A. BUSH
IPC: B64D37/32
Abstract: An assembly of fuel tank and bubbler system comprises a fuel tank defining a storage volume adapted to receive fuel therein. The fuel tank comprises at least one fuel inlet, at least one fuel outlet, and at least one gas inlet adapted to be connected to an inert gas source to feed inert gas to fill an ullage in the storage volume. A bubbler system has at least one pipe extending into the fuel tank and adapted to be immersed into the fuel of the fuel tank. The pipe has a porous structure. The pipe is adapted to be connected to an inert gas source to inject inert gas via the porous structure into the fuel of the fuel tank. A method for treating fuel in a fuel tank is also provided.
Abstract translation: 燃料箱和起泡器系统的组件包括限定适于在其中接收燃料的存储容积的燃料箱。 燃料箱包括至少一个燃料入口，至少一个燃料出口和至少一个气体入口，适于连接到惰性气体源以供入惰性气体以填充存储容积中的空白。 起泡器系统具有延伸到燃料箱中并且适于浸入燃料箱的燃料中的至少一个管。 管道具有多孔结构。 管道适于连接到惰性气体源，以通过多孔结构将惰性气体注入到燃料箱的燃料中。 还提供了一种用于处理燃料箱中的燃料的方法。
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Patent Agency Ranking
6.发明申请公开(公告)号：US20230083847A1
公开(公告)日：2023-03-16
申请号：US17989247
申请日：2022-11-17
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： James Robert JARVO , Cédric SAINTIGNAN , Joseph Daniel Maxim CIRTWILL , Kian MCCALDON , Marc-Andre TREMBLAY , David WADDLETON
Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to a combustor by supplying fuel to a first fuel manifold and a second fuel manifold of the gas turbine engine. The method also includes, while supplying fuel to the combustor by supplying fuel to the first fuel manifold: stopping supplying fuel to the second fuel manifold; and supplying pressurized air to the second fuel manifold to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated fuel nozzles.
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公开(公告)号：US20180066552A1
公开(公告)日：2018-03-08
申请号：US15418932
申请日：2017-01-30
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David WADDLETON , Daniel Matthew MCGUIRE
Abstract: A method of distributing oil to a component within a gas turbine engine includes directing a first oil flow from an oil source to an engine component and back to the oil source, directing a second oil flow from the oil source to a generator driven by the engine and back to the oil source, monitoring a parameter of the second oil flow downstream of the generator and upstream of the oil source, detecting a contaminant in the second oil flow based on the parameter, and reducing the second oil flow to the generator when the contaminant is detected without reducing the first oil flow to the engine component. A shared oil system for a component of a gas turbine engine and a generator driven by the gas turbine engine is also discussed.
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公开(公告)号：US20170361919A1
公开(公告)日：2017-12-21
申请号：US15185539
申请日：2016-06-17
Applicant: Pratt & Whitney Canada Corp.
Inventor： David WADDLETON
IPC: B64C11/38 , F04D29/36 , F04D29/32 , F04D29/58 , F04D29/063
CPC classification number: B64C11/38 , B64C11/385 , B64C27/64 , F04D29/063 , F04D29/325 , F04D29/362 , F04D29/582 , F15B21/042 , F15B2211/50536 , F15B2211/611 , F15B2211/62
Abstract: A control circuit for changing the angle of propeller blades includes a propeller control unit controlling a supply of oil to modify an angle of propeller blades, and a fixed-displacement pump providing the supply of oil from an engine oil return system to the propeller control unit. An oil cooling line extends between an outlet of the pump and the engine oil return system. The oil cooling line defines an oil leakage path leading to the engine oil return system for cooling the oil. A flow regulator between the pump and the propeller control unit is operable between an open position where oil is directed through the oil cooling line to the engine oil return system for cooling the oil, and a closed position blocking the oil cooling line and directing oil toward the propeller control unit to modify the angle of the propeller blades.
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公开(公告)号：US20250146461A1
公开(公告)日：2025-05-08
申请号：US18387258
申请日：2023-11-06
Applicant: Pratt & Whitney Canada Corp.
Inventor： David WADDLETON
Abstract: A fuel system for a gas turbine engine includes a fuel tank, a first fuel pump, an inlet ejector, and an ejector control valve. The first fuel pump includes a fuel inlet and a fuel outlet. The first fuel pump is connected in fluid communication with the fuel tank by an inlet conduit at the fuel inlet. The first fuel pump is connected in fluid communication with an outlet conduit at the fuel outlet. The inlet ejector includes an ejector nozzle disposed within the inlet conduit. The ejector control valve is connected in fluid communication between the ejector nozzle and the outlet conduit, and the ejector control valve is selectively positionable in an open position or a closed position to control a flow of fuel from the outlet conduit through the ejector nozzle to the inlet conduit.
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10.发明申请公开(公告)号：US20220298972A1
公开(公告)日：2022-09-22
申请号：US17836510
申请日：2022-06-09
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Cédric SAINTIGNAN , Joseph Daniel Maxim CIRTWILL , Kian MCCALDON , David WADDLETON , Marc-André TREMBLAY , Ignazio BROCCOLINI , Stephen TARLING
Abstract: Methods and systems of operating a gas turbine engine in a low-power condition are provided. In one embodiment, the method includes supplying fuel to the combustor by supplying fuel to the first fuel manifold via a first flow divider valve and supplying fuel to the second fuel manifold via a second flow divider valve. While supplying fuel to the combustor by supplying fuel to the first fuel manifold, the method includes stopping supplying fuel to the second fuel manifold and supplying pressurized gas to the second fuel manifold via the second flow divider valve to flush fuel in the second fuel manifold into the combustor and hinder coking in the second fuel manifold and associated nozzles.
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