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公开(公告)号：US11230979B2
公开(公告)日：2022-01-25
申请号：US16296988
申请日：2019-03-08
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Waddleton , Benjamin Renaud , Sebastien Bergeron , Etienne Plamondon , Jean-Gabriel Gauvreau
Abstract: A liquid fuel system for an aircraft engine includes a first fuel supply conduit hydraulically connected to a fuel source, a second fuel supply conduit hydraulically connected to the engine, a fuel return conduit hydraulically connected to the second fuel supply conduit, and a fuel pump. The fuel pump has a main inlet hydraulically connected to the first fuel supply conduit, an outlet hydraulically connected to the second fuel supply conduit, and an intermediate inlet hydraulically connected to the fuel return conduit. The intermediate inlet is located between the main inlet and the outlet and in use has a pressure between the main inlet pressure and the outlet pressure. A method of supplying a liquid fuel to an aircraft engine is also described.
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公开(公告)号：US11939073B2
公开(公告)日：2024-03-26
申请号：US17085006
申请日：2020-10-30
Applicant: Pratt & Whitney Canada Corp.
Inventor： Paul C. Imel , Sebastien Bergeron , Etienne Plamondon , Samuel Gosselin-Brisson , Leonid Guerchkovitch
Abstract: A method includes using an electric motor to start a thermal engine. The electric motor and thermal engine are connected to one another as the electric motor and the thermal engine of a hybrid-electric power plant in an aircraft. The electric motor can be connected to a combining gear box. The thermal engine can be connected to the combining gear box so that the electric motor and the thermal engine can provide torque to the combining gear box in a parallel hybrid-electric configuration. The combining gearbox can output torque to an air mover for providing thrust to the aircraft.
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公开(公告)号：US09981752B2
公开(公告)日：2018-05-29
申请号：US15277640
申请日：2016-09-27
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sebastien Bergeron , Pierre Gauvin , Johnny Vinski , Genevieve McMurray
CPC classification number: B64D37/08 , B64D37/14 , B64D37/32 , B65D90/34 , Y10T137/86324
Abstract: A liquid tank system comprises a main liquid tank, an outlet communicating between a fluid circuit and the main liquid tank, an inlet communicating between the fluid circuit and the main liquid tank, and an auxiliary cavity. First vent passage and second vent passage(s) communicate between the main liquid tank and the auxiliary cavity and allows liquid and gas to flow from the main liquid tank to the auxiliary cavity. The second vent passage has a flow control device regulating flow through the second vent passage and having a set point at which it allows liquid and gas to flow from the main liquid tank to the auxiliary cavity only when a pressure in the main liquid tank is beyond a threshold. The liquid tank system has an attitude envelope in which the liquid tank system is configured such that, in use, the flow control device blocks flow through the second vent passage when an end of the first vent passage in the main liquid tank is above a liquid level, and the flow control device allows gas and/or fluid flow through the second vent passage when main fluid tank pressure is above the threshold and the end of the first vent passage in the main liquid tank is below the liquid level.
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公开(公告)号：US11092126B2
公开(公告)日：2021-08-17
申请号：US16558847
申请日：2019-09-03
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sebastien Bergeron , Etienne Plamondon , Jean-Gabriel Gauvreau , Benjamin Renaud
Abstract: A method of operating an aircraft engine of an aircraft, the aircraft engine having a common-rail fuel injection system for injecting fuel into a combustion chamber of the aircraft engine, including: pressurizing fuel for circulation through the common-rail injection system; circulating a portion of the pressurized fuel through a motive flow inlet of an ejector pump; and entraining a flow through the ejector pump with the portion of the pressurized fuel circulating through the motive flow inlet.
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公开(公告)号：US10738749B1
公开(公告)日：2020-08-11
申请号：US16294160
申请日：2019-03-06
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sebastien Bergeron , Etienne Plamondon , Jean-Gabriel Gauvreau , Benjamin Renaud
Abstract: There is disclosed a method of de-icing a component of an engine assembly having a common-rail fuel injection system, including: pressurizing fuel to circulate the fuel through the common-rail injection system; drawing a portion of the fuel upstream of common-rail injectors of the common-rail injection system and directing a remainder of the fuel toward the common-rail injectors; and transferring heat from the drawn portion of the fuel to the component.
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Patent Agency Ranking
公开(公告)号：US11459958B2
公开(公告)日：2022-10-04
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：US20220135240A1
公开(公告)日：2022-05-05
申请号：US17085006
申请日：2020-10-30
Applicant: Pratt & Whitney Canada Corp.
Inventor： Paul C. Imel , Sebastien Bergeron , Etienne Plamondon , Samuel Gosselin-Brisson , Leonid Guerchkovitch
Abstract: A method includes using an electric motor to start a thermal engine. The electric motor and thermal engine are connected to one another as the electric motor and the thermal engine of a hybrid-electric power plant in an aircraft. The electric motor can be connected to a combining gear box. The thermal engine can be connected to the combining gear box so that the electric motor and the thermal engine can provide torque to the combining gear box in a parallel hybrid-electric configuration. The combining gearbox can output torque to an air mover for providing thrust to the aircraft.
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公开(公告)号：US11280342B2
公开(公告)日：2022-03-22
申请号：US16376320
申请日：2019-04-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： David Waddleton , Benjamin Renaud , Sebastien Bergeron , Etienne Plamondon , Jean-Gabriel Gauvreau
Abstract: A method of controlling a delivery pressure of an aircraft engine fuel system includes operating a rotodynamic fuel pump hydraulically connected to the fuel system to pump a fluid from an inlet of the rotodynamic pump and out of an outlet of the rotodynamic pump for delivery to the fuel system. The method further includes varying an angular relationship between the inlet and the outlet of the pump to control the delivery pressure. An aircraft engine fuel system and a rotodynamic pump are also described.
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公开(公告)号：US11111848B1
公开(公告)日：2021-09-07
申请号：US16890660
申请日：2020-06-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sebastien Bergeron , Etienne Plamondon , Jean Thomassin
Abstract: A fuel injection system for an aircraft engine has: a first fuel injector having a first actuation inlet, a first fuel inlet connected to a fuel source, and a first fuel outlet connected to the at least one combustion chamber, the first fuel injector defining a first pressure ratio; a second fuel injector having a second actuation inlet, a second fuel inlet connected to the fuel source, and a second fuel outlet connected to the at least one combustion chamber, the second fuel injector defining a second pressure ratio; and an actuation fluid system having a circuit connected to the first actuation inlet and to the second actuation inlet, the first outlet pressure different than the second outlet pressure by having one or both of the first pressure ratio different than the second pressure ratio and a first actuation pressure different than a second actuation pressure.
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公开(公告)号：US20180312271A1
公开(公告)日：2018-11-01
申请号：US15969270
申请日：2018-05-02
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Sebastien Bergeron , Pierre Gauvin , Johnny Vinski , Genevieve McMurray
CPC classification number: B64D37/08 , B64D33/00 , B64D37/10 , B64D37/14 , B64D37/32 , B65D90/34 , Y10T137/86324
Abstract: A liquid tank system comprises a main liquid tank, an outlet communicating between a fluid circuit and the main liquid tank, an inlet communicating between the fluid circuit and the main liquid tank, and an auxiliary cavity. First vent passage and second vent passage(s) communicate between the main liquid tank and the auxiliary cavity and allows liquid and gas to flow from the main liquid tank to the auxiliary cavity. The second vent passage has a flow control device regulating flow through the second vent passage and having a set point at which it allows liquid and gas to flow from the main liquid tank to the auxiliary cavity only when a pressure in the main liquid tank is beyond a threshold. The liquid tank system has an attitude envelope in which the liquid tank system is configured such that, in use, the flow control device blocks flow through the second vent passage when an end of the first vent passage in the main liquid tank is above a liquid level, and the flow control device allows gas and/or fluid flow through the second vent passage when main fluid tank pressure is above the threshold and the end of the first vent passage in the main liquid tank is below the liquid level.
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