US2545856A - Temperature controlled fuel pump for gas turbines - Google Patents
Temperature controlled fuel pump for gas turbines Download PDFInfo
- Publication number
- US2545856A US2545856A US73654A US7365449A US2545856A US 2545856 A US2545856 A US 2545856A US 73654 A US73654 A US 73654A US 7365449 A US7365449 A US 7365449A US 2545856 A US2545856 A US 2545856A
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- Prior art keywords
- fuel
- valve
- pump
- temperature
- outlet
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
- F02C9/26—Control of fuel supply
- F02C9/46—Emergency fuel control
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04C—ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT MACHINES FOR LIQUIDS; ROTARY-PISTON, OR OSCILLATING-PISTON, POSITIVE-DISPLACEMENT PUMPS
- F04C2/00—Rotary-piston machines or pumps
- F04C2/08—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing
- F04C2/12—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type
- F04C2/14—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons
- F04C2/18—Rotary-piston machines or pumps of intermeshing-engagement type, i.e. with engagement of co-operating members similar to that of toothed gearing of other than internal-axis type with toothed rotary pistons with similar tooth forms
Definitions
- the object of this invention is to transfer auto-' matically suflicient heat units from a pump to keep the temperature of the fluid below a clangerous critical point.
- a further object of this invention is to provide a main pump and an emergency pump combina tion such that fuel is furnished to the engine fuel control unit under conditions of partial or complete failure of the main fuel pump.
- FIG. 1 The figure shows diagrammatically the preferred form of my invention asapplied to a gas turbine engine.
- One of the objects of this invention is to keep the temperature of the fuel being bypassed by the engine fuel control below that temperature at which vapor lock in the common pump inlet line H] or cavitation in the pumping elements would occur.
- I is the common fuel entrance to primary pump l2 and the emergenc pump I4.
- I6 is a check valve in the outlet from pump 2, I8
- I8 is a fuel transfer pump supplying fuel from the fuel tank 82 to the main and primary fuel pump inlet line 10.
- 82 is a bypass valve around transfer pump 13.
- An emergency pump [4 delivers fuel to the passage 44 and to the passage 40 through a check valve 42 whenever the unloading valve 36 closes the unloading passage 84.
- the gas turbine 60 is provided with a compressor 62 revolving on a shaft 64 which carries the gas turbine 66.
- a shaft 64 which carries the gas turbine 66.
- Two of the combustion chambers 6B and 10 are shown, actually there are quite a number of others.
- the pipe 32 is provided with burnersfor each of the combustion chambers.
- the chamber 12 encloses the temperature responsive element 54.
- the products of combustion circulate through the chamber 12 entering passage 14 and issue out of passage 16.
- Fuel supply pump 78 draws its fuel from the tank 82' into which the receiving tank 2
- Control valve 20, having a port 88, in the pump fuel outlet passage 24 is a rotary valve actuated by a thermostat element 86 also located in fuel outlet passage 24. Valve 20 returns fuel to the fuel tank 80 through passage 22 when open.
- valve 28 closes and as the temperature of the exhaust gases increase the element 54 which is liquid filled expands and at any given revolutions per minute the speed mand of fuel valve It or if pump 92 fails, valve 30 tends to close the unloading valve 36 against the action of the pressure in passages 38 and 453.
- the valve 28 may be controlled by any one of a large number of available controls. I have chosen to illustrate this invention with a conventional control consisting of a centrifugal gov- 26 closes and the lessened pressure differential between passages 38 and 30 together with spring 46 causes valve 35 to close and pump l4 supplies fuel to the fuel system. When this occurs valve 36 takes over the function of valve 26 to maintain a very slightly lower pressure drop across valve 28. If main pump [2 fails completely, pressure in line 40, from pump l4 closes check valve I 6. The check valve 42 is closed at all times when pump I4 is not delivering fuel to passage 40.
- a pumping system for a fuel supply to a prime mover comprising a source of fuel, a main fuel pump having an outlet, a thermostatically controlled fuel valve located in the said fuel outlet and responsive to the temperature of the fuel flowing past said valve, a return passage connected to said outlet controlled by said fuel valve and discharging into said fuel source, an emergency fuel pulnp arranged in parallel to said main fuel pump so as to discharge into the outlet from said main fuel pump, a non-return check valve at the point of discharge, an unloading valve for said emergency pump, yieldable means forclosing said unloading valve, means responsive to the pressure in the outlet from said main fuel pump to hold said unloading valve open in opposition to said yieldable means until the pressure in the outlet from said main fuel pump falls due to the opening of said thermostatically controlled valve or to the failure of said primary pump.
- Fuel control means for a gas turbine of the type in which an air pump driven by said turbine supplied compressed air to a combustion chamber comprising a main fuel pump and an emergency fuel pump arranged in parallel, a common outlet from said pumps, a control valve in said outlet, control means for said valve, an unloading valve for said emergency pump comprising a moving wall connected to said unloading valve, a chamber on one side of said moving wall connected to the pressure upstream of said control valve, a chamber on the other side connected to the downstream side of such control valve, yieldable means engaging with said unloading valve and opposing the motion of said moving wall in response to the pressure drop at said control valve, a non-return valve located in the outlets from each of said pumps.
- a device as set forth in claim 2 in which there is a thermostatically operated additional control valve located in the common fuel outlet from said pumps responsive to the temperature of the fuel in the fuel outlet, a return fuel passage connected to said outlet and controlled by said additional control valve and discharging into said fuel source.
- a device as set forth in claim 2 in which there is a speed responsive device driven by said prime mover and connected to said control valve so as to tend to close the control valve at high speeds of said prime mover.
- a device as set forth in claim 2 in which there is a chamber in restricted communication with the combustion chamber downstream of the point of combustion and in unrestricted communication with the exhaust outlet downstream of said gas turbine, a temperature responsive element in said chamber linkage connecting said element to said control valve so as to move said valve into its flow restricting position as the temperature in said combustion chamber increases.
- a device as set forth in claim 2 in which there is a speed responsive device driven by said prime mover and connected to said control valve so as to tend to close the control valve at high speeds of said prime mover and in which there is a chamber in restricted communication with the combustion chamber downstream of the point of combustion and in unrestricted communication with the exhaust outlet downstream of said gas turbine, a temperature responsive element in said chamber linkage connecting said element to said control valve so as to move said valve into its flow restricting position as the temperature in said combustion chamber increases.
- a device as set forth in claim 2 in which there are temperature responsive means responsive to the temperature in said combustion chamber connected to said control valve so as to move said valve into its flow restricting position as the said temperature increases.
- a device as set forth in claim 2 in which there is a speed responsive device driven by said prime mover and connected to said control valve so as to tend to close the control valve at high speeds of said prime mover and in which there are temperature responsive means responsive to the temperature in said combustion chamber connected to said control valve so as to move said valve into its flow restricting position as the said temperature increases.
- a pumping system for a fuel supply to a prime mover comprising a source of fuel, a main fuel pump, an outlet therefrom, a non-return valve therein, an emergency fuel pump, an outlet therefrom, a non-return valve therein, a common outlet passage from both pumps downstream from said non-return valves, a thermostatically controlled fuel valve located therein responsive to the temperature of the fuel flowing therethrough, a return passage connected to said common outlet controlled by said thermostatically controlled fuel valve and discharging into said fuel source, a second control valve located in the discharge end of said common outlet passage.
- a device as set forth in claim 9 in which there is an unloading valve for said emergency pump comprising a moving wall connected to said unloading valve, a chamber on one side of said moving wall connected to the pressure upstream of said second control valve, a chamber on the other side connected to the downstream side of said second control valve, yieldable means engaging with said unloading valve and opposing the motion of said moving wall in response to the pressure drop at said second control valve which tends to open the unloading valve.
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Non-Positive-Displacement Pumps (AREA)
Description
March 20, 1951 A. w. ORR, JR
TEMPERATURE CONTROLLED FUEL PUMP FOR GAS TURBINES Filed Jan. 29, 1949 14. W Orr Jr.
Patented Mar. 20, 1951 TEMPERATURE CONTROLLED FUEL PUMP FOR GAS TURBINES Andrew William Orr, Jr., Detroit, Mich., assignor to George M. Holley and Earl Holley Application January 29, 1949, Serial No. 73,654
'10 Claims. (Cl. 10311) The object of this invention is to transfer auto-' matically suflicient heat units from a pump to keep the temperature of the fluid below a clangerous critical point.
A further object of this invention is to provide a main pump and an emergency pump combina tion such that fuel is furnished to the engine fuel control unit under conditions of partial or complete failure of the main fuel pump.
\ The figure shows diagrammatically the preferred form of my invention asapplied to a gas turbine engine.
One of the objects of this invention is to keep the temperature of the fuel being bypassed by the engine fuel control below that temperature at which vapor lock in the common pump inlet line H] or cavitation in the pumping elements would occur. I
In the figure, I is the common fuel entrance to primary pump l2 and the emergenc pump I4. I6 is a check valve in the outlet from pump 2, I8
is a safety bypass valve from pump l2 leading back to the pump inlet I0, 48 is a check valve 'in the outlet from pump 14 leading backto the pump inlet l8.
I8 is a fuel transfer pump supplying fuel from the fuel tank 82 to the main and primary fuel pump inlet line 10. 82 is a bypass valve around transfer pump 13.
.by the pressure transmitted through a passage 38 connected to a passage 40. An emergency pump [4 delivers fuel to the passage 44 and to the passage 40 through a check valve 42 whenever the unloading valve 36 closes the unloading passage 84.
A spring 46 together withthe pressure in line 2 The gas turbine 60 is provided with a compressor 62 revolving on a shaft 64 which carries the gas turbine 66. Two of the combustion chambers 6B and 10 are shown, actually there are quite a number of others. The pipe 32 is provided with burnersfor each of the combustion chambers.
The chamber 12 encloses the temperature responsive element 54. The products of combustion circulate through the chamber 12 entering passage 14 and issue out of passage 16.
Fuel supply pump 78 draws its fuel from the tank 82' into which the receiving tank 2| discharges.
Operation Assume that the emergency pump I4 is out of action, as shown, and that the normal pump 12 is supplying the fuel to run the gas turbine. As the speed increases the valve 28 closes and as the temperature of the exhaust gases increase the element 54 which is liquid filled expands and at any given revolutions per minute the speed mand of fuel valve It or if pump 92 fails, valve 30 tends to close the unloading valve 36 against the action of the pressure in passages 38 and 453.
The valve 28 may be controlled by any one of a large number of available controls. I have chosen to illustrate this invention with a conventional control consisting of a centrifugal gov- 26 closes and the lessened pressure differential between passages 38 and 30 together with spring 46 causes valve 35 to close and pump l4 supplies fuel to the fuel system. When this occurs valve 36 takes over the function of valve 26 to maintain a very slightly lower pressure drop across valve 28. If main pump [2 fails completely, pressure in line 40, from pump l4 closes check valve I 6. The check valve 42 is closed at all times when pump I4 is not delivering fuel to passage 40.
Under these conditions when pumps l2 and M are running athigh speed and valve 28 is almost closed, most of the fuel delivery is bypassed back to pump inlet ill by valve 26 through passage 34. Alternatively when pump l2'is not operating then the bypass valve 36' controls the flow through passage and pump l4 delivers fuel to the main fuel control valve 28. Either of these conditions results in the addition of considerable heat to the fuel system and a rise in temperature of the fuel in the critical inlet passage 10. When the temperature rises to a point below where vapor lock or cavitation would take place, thermostat element 86 rotates and opens the port 88 in the rotary valve 20 thereby passing fuel back to the fuel tank 80 through passage 22. Colder fuel from the tank 80 is thus brought into the system to reduce the temperature of the fuel below the critical point.
What I claim is:
l. A pumping system for a fuel supply to a prime mover comprising a source of fuel, a main fuel pump having an outlet, a thermostatically controlled fuel valve located in the said fuel outlet and responsive to the temperature of the fuel flowing past said valve, a return passage connected to said outlet controlled by said fuel valve and discharging into said fuel source, an emergency fuel pulnp arranged in parallel to said main fuel pump so as to discharge into the outlet from said main fuel pump, a non-return check valve at the point of discharge, an unloading valve for said emergency pump, yieldable means forclosing said unloading valve, means responsive to the pressure in the outlet from said main fuel pump to hold said unloading valve open in opposition to said yieldable means until the pressure in the outlet from said main fuel pump falls due to the opening of said thermostatically controlled valve or to the failure of said primary pump.
2. Fuel control means for a gas turbine of the type in which an air pump driven by said turbine supplied compressed air to a combustion chamber comprising a main fuel pump and an emergency fuel pump arranged in parallel, a common outlet from said pumps, a control valve in said outlet, control means for said valve, an unloading valve for said emergency pump comprising a moving wall connected to said unloading valve, a chamber on one side of said moving wall connected to the pressure upstream of said control valve, a chamber on the other side connected to the downstream side of such control valve, yieldable means engaging with said unloading valve and opposing the motion of said moving wall in response to the pressure drop at said control valve, a non-return valve located in the outlets from each of said pumps.
3. A device as set forth in claim 2 in which there is a thermostatically operated additional control valve located in the common fuel outlet from said pumps responsive to the temperature of the fuel in the fuel outlet, a return fuel passage connected to said outlet and controlled by said additional control valve and discharging into said fuel source.
4. A device as set forth in claim 2 in which there is a speed responsive device driven by said prime mover and connected to said control valve so as to tend to close the control valve at high speeds of said prime mover.
5. A device as set forth in claim 2 in which there is a chamber in restricted communication with the combustion chamber downstream of the point of combustion and in unrestricted communication with the exhaust outlet downstream of said gas turbine, a temperature responsive element in said chamber linkage connecting said element to said control valve so as to move said valve into its flow restricting position as the temperature in said combustion chamber increases.
6. A device as set forth in claim 2 in which there is a speed responsive device driven by said prime mover and connected to said control valve so as to tend to close the control valve at high speeds of said prime mover and in which there is a chamber in restricted communication with the combustion chamber downstream of the point of combustion and in unrestricted communication with the exhaust outlet downstream of said gas turbine, a temperature responsive element in said chamber linkage connecting said element to said control valve so as to move said valve into its flow restricting position as the temperature in said combustion chamber increases.
7. A device as set forth in claim 2 in which there are temperature responsive means responsive to the temperature in said combustion chamber connected to said control valve so as to move said valve into its flow restricting position as the said temperature increases.
8. A device as set forth in claim 2 in which there is a speed responsive device driven by said prime mover and connected to said control valve so as to tend to close the control valve at high speeds of said prime mover and in which there are temperature responsive means responsive to the temperature in said combustion chamber connected to said control valve so as to move said valve into its flow restricting position as the said temperature increases.
9. A pumping system for a fuel supply to a prime mover comprising a source of fuel, a main fuel pump, an outlet therefrom, a non-return valve therein, an emergency fuel pump, an outlet therefrom, a non-return valve therein, a common outlet passage from both pumps downstream from said non-return valves, a thermostatically controlled fuel valve located therein responsive to the temperature of the fuel flowing therethrough, a return passage connected to said common outlet controlled by said thermostatically controlled fuel valve and discharging into said fuel source, a second control valve located in the discharge end of said common outlet passage.
10. A device as set forth in claim 9 in which there is an unloading valve for said emergency pump comprising a moving wall connected to said unloading valve, a chamber on one side of said moving wall connected to the pressure upstream of said second control valve, a chamber on the other side connected to the downstream side of said second control valve, yieldable means engaging with said unloading valve and opposing the motion of said moving wall in response to the pressure drop at said second control valve which tends to open the unloading valve.
ANDREW WILLIAM ORR, JR.
REFERENCES CITED The following references are of record in the file of this patent:
UNITED STATES PATENTS Number Name 7 Date 832,620 Noyes Oct. 9, 1906 1,423,759 Doble July 25, 1922
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US73654A US2545856A (en) | 1949-01-29 | 1949-01-29 | Temperature controlled fuel pump for gas turbines |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US73654A US2545856A (en) | 1949-01-29 | 1949-01-29 | Temperature controlled fuel pump for gas turbines |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US2545856A true US2545856A (en) | 1951-03-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US73654A Expired - Lifetime US2545856A (en) | 1949-01-29 | 1949-01-29 | Temperature controlled fuel pump for gas turbines |
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Cited By (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2677930A (en) * | 1950-10-23 | 1954-05-11 | Phillips Petroleum Co | Device for control of dual fuel systems for gas turbines |
| US2707866A (en) * | 1949-04-27 | 1955-05-10 | Thompson Prod Inc | Jet engine fuel control system responsive to engine speed and tail pipe temperature |
| US2708826A (en) * | 1949-03-30 | 1955-05-24 | United Aircraft Corp | Fuel control for gas turbine |
| US2727356A (en) * | 1950-04-17 | 1955-12-20 | Bendix Aviat Corp | Control system for starting an aircraft engine |
| US2731794A (en) * | 1956-01-24 | torell | ||
| US2740255A (en) * | 1950-09-20 | 1956-04-03 | Bendix Aviat Corp | Single lever control mechanism for aircraft engine |
| US2740469A (en) * | 1950-04-14 | 1956-04-03 | Chrysler Corp | Flow control apparatus |
| US2741086A (en) * | 1950-04-26 | 1956-04-10 | Bendix Aviat Corp | Automatic starter control |
| US2761280A (en) * | 1950-08-31 | 1956-09-04 | Daniel G Russ | Fuel-air control mechanism for metering flow of fuel to afterburners in jet or turbine engines |
| US2762305A (en) * | 1952-12-04 | 1956-09-11 | New York Air Brake Co | Variable delivery pump system, including a standby unit |
| US2774215A (en) * | 1949-04-22 | 1956-12-18 | Bendix Aviat Corp | Tailpipe or afterburning control for turbojet engines |
| US2780172A (en) * | 1952-04-26 | 1957-02-05 | United Aircraft Corp | Dual fuel pump |
| US2806352A (en) * | 1951-09-28 | 1957-09-17 | Bendix Aviat Corp | Fuel control system responsive to engine temperature and speed conditions |
| US2815714A (en) * | 1951-12-29 | 1957-12-10 | Gen Electric | Liquid flow delivery system |
| US2820340A (en) * | 1952-12-30 | 1958-01-21 | Gen Motors Corp | Turbojet engine fuel and nozzle control system |
| US2835323A (en) * | 1953-10-13 | 1958-05-20 | Plessey Co Ltd | Fuel systems for internal combustion engines and gas turbines |
| US2852913A (en) * | 1951-10-15 | 1958-09-23 | Gen Motors Corp | Automatic mechanism for controlling fuel flow to a jet engine |
| US2865166A (en) * | 1952-06-11 | 1958-12-23 | Gen Motors Corp | Afterburner fuel system with pump unloader |
| US2917110A (en) * | 1956-10-11 | 1959-12-15 | Gen Motors Corp | Vapor lock preventing device |
| US2918790A (en) * | 1955-11-25 | 1959-12-29 | Grovar Inc | Gas turbine power plant system |
| US2924940A (en) * | 1956-11-19 | 1960-02-16 | Gen Motors Corp | Pump control system |
| US2944597A (en) * | 1957-02-20 | 1960-07-12 | Thompson Ramo Wooldridge Inc | Fuel system |
| US2955609A (en) * | 1955-11-30 | 1960-10-11 | Gen Motors Corp | Dual pump fuel system |
| US2965118A (en) * | 1955-04-29 | 1960-12-20 | Fairchild Engine & Airplane | Fluid pressure ratio control device |
| US2968348A (en) * | 1957-10-03 | 1961-01-17 | United Aircraft Corp | Multi-pump system having speed and pressure rise responsive by-pass means |
| US2971575A (en) * | 1955-04-14 | 1961-02-14 | Bendix Corp | Fuel flow control for engines |
| US2981271A (en) * | 1954-06-01 | 1961-04-25 | Holley Carburetor Co | Gas turbine isochronous governor |
| US2988885A (en) * | 1956-04-06 | 1961-06-20 | Bendix Corp | Pump control |
| US3033277A (en) * | 1955-05-09 | 1962-05-08 | Holley Carburetor Co | Fuel supply system |
| US3086581A (en) * | 1960-01-08 | 1963-04-23 | Orenda Engines Ltd | Fuel pumping systems for aircraft engines |
| US3092966A (en) * | 1957-07-05 | 1963-06-11 | Bendix Corp | Governor for gas turbine engines including inlet condition bias during steady state operation |
| US3154921A (en) * | 1962-01-19 | 1964-11-03 | Caterpillar Tractor Co | Fluid pressure system and control |
| US3267670A (en) * | 1963-12-13 | 1966-08-23 | Bendix Corp | Gas turbine engine control |
| US3294148A (en) * | 1966-12-27 | Fuel feeding system for internal combustion engines | ||
| FR2169244A1 (en) * | 1972-01-26 | 1973-09-07 | Trw Inc |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US832620A (en) * | 1905-10-12 | 1906-10-09 | Edward P Noyes | Thermostatic level-controller. |
| US1423759A (en) * | 1918-05-15 | 1922-07-25 | Doble Lab | Apparatus for controlling the flow of water to boilers |
-
1949
- 1949-01-29 US US73654A patent/US2545856A/en not_active Expired - Lifetime
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US832620A (en) * | 1905-10-12 | 1906-10-09 | Edward P Noyes | Thermostatic level-controller. |
| US1423759A (en) * | 1918-05-15 | 1922-07-25 | Doble Lab | Apparatus for controlling the flow of water to boilers |
Cited By (35)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2731794A (en) * | 1956-01-24 | torell | ||
| US3294148A (en) * | 1966-12-27 | Fuel feeding system for internal combustion engines | ||
| US2708826A (en) * | 1949-03-30 | 1955-05-24 | United Aircraft Corp | Fuel control for gas turbine |
| US2774215A (en) * | 1949-04-22 | 1956-12-18 | Bendix Aviat Corp | Tailpipe or afterburning control for turbojet engines |
| US2707866A (en) * | 1949-04-27 | 1955-05-10 | Thompson Prod Inc | Jet engine fuel control system responsive to engine speed and tail pipe temperature |
| US2740469A (en) * | 1950-04-14 | 1956-04-03 | Chrysler Corp | Flow control apparatus |
| US2727356A (en) * | 1950-04-17 | 1955-12-20 | Bendix Aviat Corp | Control system for starting an aircraft engine |
| US2741086A (en) * | 1950-04-26 | 1956-04-10 | Bendix Aviat Corp | Automatic starter control |
| US2761280A (en) * | 1950-08-31 | 1956-09-04 | Daniel G Russ | Fuel-air control mechanism for metering flow of fuel to afterburners in jet or turbine engines |
| US2740255A (en) * | 1950-09-20 | 1956-04-03 | Bendix Aviat Corp | Single lever control mechanism for aircraft engine |
| US2677930A (en) * | 1950-10-23 | 1954-05-11 | Phillips Petroleum Co | Device for control of dual fuel systems for gas turbines |
| US2806352A (en) * | 1951-09-28 | 1957-09-17 | Bendix Aviat Corp | Fuel control system responsive to engine temperature and speed conditions |
| US2852913A (en) * | 1951-10-15 | 1958-09-23 | Gen Motors Corp | Automatic mechanism for controlling fuel flow to a jet engine |
| US2815714A (en) * | 1951-12-29 | 1957-12-10 | Gen Electric | Liquid flow delivery system |
| US2780172A (en) * | 1952-04-26 | 1957-02-05 | United Aircraft Corp | Dual fuel pump |
| US2865166A (en) * | 1952-06-11 | 1958-12-23 | Gen Motors Corp | Afterburner fuel system with pump unloader |
| US2762305A (en) * | 1952-12-04 | 1956-09-11 | New York Air Brake Co | Variable delivery pump system, including a standby unit |
| US2820340A (en) * | 1952-12-30 | 1958-01-21 | Gen Motors Corp | Turbojet engine fuel and nozzle control system |
| US2835323A (en) * | 1953-10-13 | 1958-05-20 | Plessey Co Ltd | Fuel systems for internal combustion engines and gas turbines |
| US2981271A (en) * | 1954-06-01 | 1961-04-25 | Holley Carburetor Co | Gas turbine isochronous governor |
| US2971575A (en) * | 1955-04-14 | 1961-02-14 | Bendix Corp | Fuel flow control for engines |
| US2965118A (en) * | 1955-04-29 | 1960-12-20 | Fairchild Engine & Airplane | Fluid pressure ratio control device |
| US3033277A (en) * | 1955-05-09 | 1962-05-08 | Holley Carburetor Co | Fuel supply system |
| US2918790A (en) * | 1955-11-25 | 1959-12-29 | Grovar Inc | Gas turbine power plant system |
| US2955609A (en) * | 1955-11-30 | 1960-10-11 | Gen Motors Corp | Dual pump fuel system |
| US2988885A (en) * | 1956-04-06 | 1961-06-20 | Bendix Corp | Pump control |
| US2917110A (en) * | 1956-10-11 | 1959-12-15 | Gen Motors Corp | Vapor lock preventing device |
| US2924940A (en) * | 1956-11-19 | 1960-02-16 | Gen Motors Corp | Pump control system |
| US2944597A (en) * | 1957-02-20 | 1960-07-12 | Thompson Ramo Wooldridge Inc | Fuel system |
| US3092966A (en) * | 1957-07-05 | 1963-06-11 | Bendix Corp | Governor for gas turbine engines including inlet condition bias during steady state operation |
| US2968348A (en) * | 1957-10-03 | 1961-01-17 | United Aircraft Corp | Multi-pump system having speed and pressure rise responsive by-pass means |
| US3086581A (en) * | 1960-01-08 | 1963-04-23 | Orenda Engines Ltd | Fuel pumping systems for aircraft engines |
| US3154921A (en) * | 1962-01-19 | 1964-11-03 | Caterpillar Tractor Co | Fluid pressure system and control |
| US3267670A (en) * | 1963-12-13 | 1966-08-23 | Bendix Corp | Gas turbine engine control |
| FR2169244A1 (en) * | 1972-01-26 | 1973-09-07 | Trw Inc |
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