Fuel delivery and control system including a positive displacement actuation pump with a variable pressure regulator supplementing a fixed displacement main fuel pump
원문보기
IPC분류정보
국가/구분
United States(US) Patent
등록
국제특허분류(IPC7판)
F02C-001/00
출원번호
US-0251930
(2008-10-15)
등록번호
US-8302406
(2012-11-06)
발명자
/ 주소
Baker, Carthel C.
출원인 / 주소
Woodward, Inc.
대리인 / 주소
Reinhart Boerner Van Deuren P.C.
인용정보
피인용 횟수 :
5인용 특허 :
11
초록▼
A fuel delivery and control system is provided including a dual pump fluid circuit configuration comprising a fixed positive displacement pump sized to supply the main engine burn flow ranging from above windmill through cruise, a positive displacement actuation pump including a variable pressure re
A fuel delivery and control system is provided including a dual pump fluid circuit configuration comprising a fixed positive displacement pump sized to supply the main engine burn flow ranging from above windmill through cruise, a positive displacement actuation pump including a variable pressure regulator, wherein the actuation pump is sized to supply fluid to engine actuators, valves and other hydraulically operated engine components and a pump flow sharing system interconnecting the two pumps. The combined flow from the two pumps is sufficient to meet the engine flow demand for windmill relight and maximum flow conditions. During cruise or normal operating conditions, the pumps operate in completely isolated flow circuits, minimizing recirculation and therefore heat input into the fuel supply system.
대표청구항▼
1. A fuel delivery and control system for a gas turbine engine having a maximum fuel flow requirement and a steady state requirement that is less than the maximum fuel flow requirement and also including a fuel metering unit, the fuel delivery and control system comprising: a fixed displacement actu
1. A fuel delivery and control system for a gas turbine engine having a maximum fuel flow requirement and a steady state requirement that is less than the maximum fuel flow requirement and also including a fuel metering unit, the fuel delivery and control system comprising: a fixed displacement actuation pump of a size limited to providing only a first portion of the maximum fuel flow requirement of the engine, the actuation pump having an inlet and an outlet;a variable pressure regulator in fluid communication with the outlet of the actuation pump, the variable regulator capable of adjusting the pressure drop across the inlet and the outlet of the actuation pump to maintain a minimum discharge pressure; anda fixed displacement main pump of a size limited to providing a second portion of the maximum fuel flow requirement of the engine, the second portion being less than the maximum fuel flow requirement of the engine, the main pump having an outlet in fluid communication with the fuel metering unit and in selective fluid communication with the outlet of the actuation pump, wherein the fuel delivery and control system is configurable between an isolated pumps mode wherein the outlets of each of the actuation pump and the main pump are separated from each other and a shared pumps mode wherein the outlets of each of the actuation pump and the main pump are in fluid communication with each other to combine the first portion of the maximum fuel flow of the engine with the second portion of the maximum fuel flow of the engine and wherein the combined flow is supplied to the fuel metering unit of the engine. 2. The fuel delivery and control system of claim 1, wherein the actuation pump is sized to provide fuel at a sufficient predetermined pressure and flow rate to a plurality of hydraulically actuated devices within the engine in addition to the first portion of the maximum fuel flow requirement. 3. The fuel delivery and control system of claim 1, wherein the main pump is configured to provide fuel to the fuel metering unit at a pressure that is greater than the discharge pressure of the actuation pump when the system is in the isolated pumps mode and the engine is operating at steady state conditions. 4. The fuel delivery and control system of claim 1, wherein the main pump is sized to provide substantially 20 percent of the maximum fuel flow requirement of the engine and the actuation pump is sized to provide substantially about 80 percent of the maximum fuel flow requirement of the engine. 5. The fuel delivery and control system of claim 1, further comprising a fuel bypass line in fluid communication with the fuel metering unit, the bypass line directing fuel back to the inlet of the main pump. 6. A fuel system for use in an aircraft engine having a maximum fuel flow demand, the fuel system comprising: a main fuel pump for pressurizing fuel from a fuel supply, the main fuel pump having an inlet and an outlet, the main fuel pump providing fuel to the engine at a predetermined flow rate and discharge pressure; andan actuation pump comprising a pressure regulator, the actuation pump having an inlet and an outlet, and capable of providing output fuel at a discharge pressure that is lower than the discharge pressure of the main pump, the outlet of the actuation pump in selective fluid communication with the outlet of the main pump, wherein the combined output flow from the main pump and the actuation pump is required in order to meet the maximum fuel demand of the engine. 7. The fuel system of claim 6, wherein a variable discharge pressure of the actuation pump is controlled to the minimum pressure sufficient to operate a plurality of hydraulically actuated devices within the engine. 8. The fuel system of claim 6, wherein the main fuel pump is sized to provide substantially 20 percent of the maximum fuel demand from the engine and the actuation pump is sized to provide substantially about 80 percent of the maximum fuel demand of the engine. 9. The fuel system of claim 6, further comprising a regulator valve assembly in communication with the actuation pump for controlling the pressure drop across the inlet and the outlet of the actuation pump. 10. The fuel system of claim 6, wherein the pressure regulator is a variable pressure regulator. 11. The fuel system of claim 6, further comprising a control valve in communication with the pressure regulator, the control valve configured for setting a pressure differential across the actuation pump. 12. The fuel system of claim 6, further comprising a pump flow sharing system selectively interconnecting the outlet of the main fuel pump and the outlet of the actuation pump when the engine burn flow fuel demand is greater than the flow rate of the main fuel pump. 13. A method of delivering fuel to an aircraft engine having a maximum fuel demand, the method comprising: providing a first pump sized for a limited supply of approximately 20% of the maximum fuel demand of the engine;providing a second pump having an outlet in selective fluid communication with an outlet of the first pump, the second pump providing approximately 80% of the maximum fuel demand of the engine; andalternating between an isolated pumps mode wherein the second pump provides fluid flow only to an actuation system and a servo system of the engine and a shared pumps mode wherein the outlets of the first and the second pumps are required to be combined provide the maximum fuel demand required by the engine. 14. The method of claim 13, wherein the second pump is a fixed displacement pump including a variable pressure regulator. 15. The method of claim 13, wherein the second pump is configured to supply a minimum discharge pressure sufficient to operate the actuation system and the servo system of the engine, the discharge pressure of the second pump being maintained lower than the first pump when the pumps are in the isolated pumps mode.
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이 특허에 인용된 특허 (11)
Markunas Albert L. (Roscoe IL), Dual pump controls.
Rannenberg George C. (Canton CT), Efficiency fluid pumping system including sequential unloading of a plurality of pumps by a single pressure responsive c.
Arline Samuel B. (Lake Park FL) Eder Matthias (Stuart FL) Dunlap Jeffrey J. (Stuart FL) Douglas Gary W. (Palm Beach Gardens FL), Fuel metering and actuation system.
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