WO2005104678B1 - Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefit - Google Patents
Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefitInfo
- Publication number
- WO2005104678B1 WO2005104678B1 PCT/US2005/010364 US2005010364W WO2005104678B1 WO 2005104678 B1 WO2005104678 B1 WO 2005104678B1 US 2005010364 W US2005010364 W US 2005010364W WO 2005104678 B1 WO2005104678 B1 WO 2005104678B1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- pump
- fuel
- displacement
- delivery system
- fuel delivery
- Prior art date
Links
- 239000000446 fuel Substances 0.000 title claims abstract 49
- 238000006073 displacement reaction Methods 0.000 title claims abstract 39
- 230000001105 regulatory Effects 0.000 claims 3
- 230000001276 controlling effect Effects 0.000 claims 1
- 238000010438 heat treatment Methods 0.000 claims 1
Abstract
A fuel delivery system (10) comprises a variable displacement pump (20) for pressurizing fuel. The variable displacement pump has a distinct first pump displacement setting for a first desired mass flow of fuel and a distinct second pump displacement setting for a second desired mass flow of fuel. The variable displacement pump operates in only one of the first and second pump displacement settings. A fuel control (22) with a metering valve downstream of the variable displacement pump selectively regulates fuel delivery.
Claims
1. (Amended) A fuel delivery system for an associated jet aircraft turbine engine during a control system failure comprising: a pump for pressurizing fuel, the pump having a distinct first pump displacement setting for a first desired mass flow of fuel and a distinct second pump displacement setting for a second desired mass flow of fuel, wherein the pump operates in only one of the first and second pump displacement settings; a metering valve downstream of the pump for selectively regulating fuel delivery; and, means for preventing engine over-thrust operatively associated with the pump for positioning the pump in the second pump displacement setting in response to a control system failure whereby pump flow to the associated engine is limited to provide over-thrust protection.
2. The fuel delivery system of claim 1 wherein the first pump displacement setting is a high mass flow displacement setting.
3. The fuel delivery system of claim 1 wherein the second pump displacement setting is a low mass flow displacement setting,
4. The fuel delivery system of claim 3 wherein the pump is activated to the second pump displacement setting in response to a control system failure.
5. A fuel delivery system for an associated jet aircraft turbine engine during a control system failure comprising: a pump for pressurizing fuel, the pump having a distinct first pump displacement setting for a first desired high mass flow of fuel and a distinct second pump displacement setting for a second desired low mass flow of fuel, wherein the pump operates in only one of the first and second pump displacement settings, wherein the pump is activated to the second pump displacement setting in response to a control system failure; a metering valve downstream of the pump for selectively regulating fuel delivery; and, a controller for preventing engine over-thrust operatively associated with the pump for positioning the pump in the second pump displacement setting in response to a control system failure whereby pump flow to the associated engine is limited to provide over-thrust protection.
6. The fuel delivery system of claim 1 wherein the pump includes distinct first and second stops defining operational parameters for pump stroke travel.
7. The fuel delivery system of claim 1 further comprising a controller for positioning the pump in one of the first and second pump displacement settings.
8. (Amended) The fuel delivery system of claim 5 or 7 wherein the controller is a solenoid valve responsive to an electronic control signal for actuating the pump to only one of the first and second pump displacement settings.
9. The fuel delivery system of claim 1 further comprising a bypass passage downstream of the pump for returning excess flow to a pump inlet.
10. The fuel delivery system of claim 1 further comprising a solenoid valve, the solenoid valve being commanded, by the electronic control for positioning the pump to one of the first and second modes of operation.
11. The fuel delivery system of claim 1 wherein the second pump displacement setting contributes less heat to the fuel system.
12. The fuel delivery system of claim 1 wherein the first pump displacement setting permits fuel system heating for avoiding fuel system icing at cold operating conditions.
13. The fuel delivery system of claim 1 wherein the pump is a variable displacement pump.
13
14. (Amended) A method of delivering fuel for an associated jet aircraft turbine engine comprising the steps of: pressurizing fuel through a pump having first and second fixed displacement settings for a first predetermined, high mass flow of fuel and a second predetermined, low mass flows of fuel; metering the fuel through a metering valve for supply to associated fuel nozzles; setting the pump to only one of the first and second displacement settings; and, positioning the pump in the second pump displacement setting in response to a control system failure whereby pump flow to the associated engine is limited to provide over-thrust protection.
15. The method of claim 14 comprising the further step of controlling fuel system temperature by operating the pump in its fixed high mass flow displacement setting.
16. The method of claim 14 comprising the further step of bypassing fuel exiting the metering valve to recirculate a portion of fuel to the pump.
17. A fuel delivery system for preventing engine over-thrust for an associated jet aircraft turbine engine comprising: a variable displacement pump for pressurizing fuel operative in either a first predetermined, high mass flow, fuel displacement setting or a second predetermined, low mass flow, fuel displacement setting; a metering valve downstream of the variable displacement pump for selectively regulating fuel delivery; and, a controller for selectively positioning the pump in only one of the first and second fuel displacement settings, and positioning the pump to operate in the second fuel displacement setting in the event of failure of the controller thereby preventing engine over-thrust.
14
18. The fuel delivery system of claim 17 wherein the pump includes first and second stops in first and second extremes of pump stroke travel.
19. The fuel delivery system of claim 18 wherein the first and second extremes of pump stroke travel define the respective first and second displacement setting.
15
Priority Applications (6)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| BRPI0509387-2A BRPI0509387A (en) | 2004-03-29 | 2005-03-29 | dual displacement configuration variable displacement pump used as protection against excessive engine propulsion with fuel system thermal benefit |
| CN2005800101302A CN1965155B (en) | 2004-03-29 | 2005-03-29 | Fuel dispensing system used for turbine engine of jet plane |
| CA2561273A CA2561273C (en) | 2004-03-29 | 2005-03-29 | Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefit |
| EP05773646.4A EP1743092B1 (en) | 2004-03-29 | 2005-03-29 | Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefit |
| US10/592,724 US7610760B2 (en) | 2004-03-29 | 2005-03-29 | Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefit |
| JP2007506441A JP2007530873A (en) | 2004-03-29 | 2005-03-29 | Variable displacement pump with double displacement capacity used to prevent over-thrust of engines with fuel system heat benefits |
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US55742904P | 2004-03-29 | 2004-03-29 | |
| US60/557,429 | 2004-03-29 |
Publications (3)
| Publication Number | Publication Date |
|---|---|
| WO2005104678A2 WO2005104678A2 (en) | 2005-11-10 |
| WO2005104678A3 WO2005104678A3 (en) | 2005-12-29 |
| WO2005104678B1 true WO2005104678B1 (en) | 2006-03-02 |
Family
ID=35242113
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| PCT/US2005/010364 WO2005104678A2 (en) | 2004-03-29 | 2005-03-29 | Two-displacement setting variable displacement pump used as engine over-thrust protection with fuel system thermal benefit |
Country Status (8)
| Country | Link |
|---|---|
| US (1) | US7610760B2 (en) |
| EP (1) | EP1743092B1 (en) |
| JP (1) | JP2007530873A (en) |
| KR (1) | KR20070012393A (en) |
| CN (1) | CN1965155B (en) |
| BR (1) | BRPI0509387A (en) |
| CA (1) | CA2561273C (en) |
| WO (1) | WO2005104678A2 (en) |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7845177B2 (en) * | 2004-09-16 | 2010-12-07 | Hamilton Sundstrand Corporation | Metering demand fuel system |
| FR2945075B1 (en) * | 2009-04-29 | 2015-06-05 | Snecma | METHOD AND DEVICE FOR FEEDING A TURBOMACHINE CHAMBER WITH A REGULATED FUEL FLOW |
| US9151180B2 (en) | 2010-06-15 | 2015-10-06 | Hamilton Sundstrand Corporation | Lubrication driven gas turbine engine actuation system |
| GB2501289A (en) * | 2012-04-18 | 2013-10-23 | Eaton Aerospace Ltd | Aircraft fuel supply system |
| CN103821617B (en) * | 2012-11-16 | 2016-08-24 | 哈尔滨飞机工业集团有限责任公司 | A kind of fuel pressurization pump control system |
| CN103557082B (en) * | 2013-10-25 | 2015-12-30 | 中国航空动力机械研究所 | A kind of engine fuel supplier and controlling method |
| FR3068114B1 (en) * | 2017-06-27 | 2019-08-16 | Safran Aircraft Engines | FLUID SUPPLY SYSTEM FOR TURBOMACHINE, COMPRISING A VARIABLE CYLINDER PUMP FOLLOWED BY A FLUID DOSER |
| US11713718B2 (en) * | 2021-09-30 | 2023-08-01 | Hamilton Sundstrand Corporation | Dual valve fluid metering system |
| US11946420B1 (en) | 2023-06-22 | 2024-04-02 | Hamilton Sundstrand Corporation | Fuel systems having thermal recirculation |
Family Cites Families (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CH266733A (en) * | 1947-01-23 | 1950-02-15 | Rolls Royce | Gas turbine plant. |
| US5715674A (en) * | 1995-12-22 | 1998-02-10 | United Technologies Corporation | Hydromechanical control for a variable delivery, positive displacement fuel pump |
| US5806300A (en) * | 1995-12-22 | 1998-09-15 | United Technologies Corporation | Electronic control for a variable delivery, positive displacement fuel pump |
| GB9910074D0 (en) * | 1999-04-30 | 1999-06-30 | Lucas Ind Plc | Fuel control system and valve therefor |
| US6487847B1 (en) * | 2000-11-03 | 2002-12-03 | General Electric Company | Gas turbine engine fuel control system |
| JP4206646B2 (en) * | 2001-04-04 | 2009-01-14 | 株式会社Ｉｈｉ | Fuel supply method and fuel supply system for gas turbine engine, and gas turbine engine |
| US7108493B2 (en) | 2002-03-27 | 2006-09-19 | Argo-Tech Corporation | Variable displacement pump having rotating cam ring |
| CN101968053B (en) * | 2001-04-05 | 2013-06-19 | 阿果技术公司 | Variable displacement pump having rotating cam ring |
| US6810674B2 (en) * | 2002-07-18 | 2004-11-02 | Argo-Tech Corporation | Fuel delivery system |
| US6962485B2 (en) * | 2003-04-14 | 2005-11-08 | Goodrich Pump And Engine Control Systems, Inc. | Constant bypass flow controller for a variable displacement pump |
| US20050100447A1 (en) * | 2003-11-11 | 2005-05-12 | Desai Mihir C. | Flow control system for a gas turbine engine |
-
2005
- 2005-03-29 BR BRPI0509387-2A patent/BRPI0509387A/en not_active IP Right Cessation
- 2005-03-29 US US10/592,724 patent/US7610760B2/en active Active
- 2005-03-29 WO PCT/US2005/010364 patent/WO2005104678A2/en active Application Filing
- 2005-03-29 CA CA2561273A patent/CA2561273C/en not_active Expired - Fee Related
- 2005-03-29 JP JP2007506441A patent/JP2007530873A/en active Pending
- 2005-03-29 KR KR1020067020360A patent/KR20070012393A/en not_active Application Discontinuation
- 2005-03-29 CN CN2005800101302A patent/CN1965155B/en not_active Expired - Fee Related
- 2005-03-29 EP EP05773646.4A patent/EP1743092B1/en active Active
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