US1052588A - Hydrocarbon power-generator. - Google Patents
Hydrocarbon power-generator. Download PDFInfo
- Publication number
- US1052588A US1052588A US62061011A US1911620610A US1052588A US 1052588 A US1052588 A US 1052588A US 62061011 A US62061011 A US 62061011A US 1911620610 A US1911620610 A US 1911620610A US 1052588 A US1052588 A US 1052588A
- Authority
- US
- United States
- Prior art keywords
- chamber
- fuel
- combustion
- air
- space
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired - Lifetime
Links
Images
Classifications
-
- 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
- F02C9/28—Regulating systems responsive to plant or ambient parameters, e.g. temperature, pressure, rotor speed
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10S—TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10S60/00—Power plants
- Y10S60/913—Collection of reggio patents
Definitions
- the main objects of this invention are to provide improved means for generating power from the combustion of hydrocarbon fuel and particularly adapted for utilizing the power due to expansion of the fuel during combustion, in such manner that the products of combustion may be used for operating a motor at comparatively low temperature; to provide in apparatus of this kind improved means for vapo-rizing liquid or powdered fuel; to provide improved means for preventing back firing in the vaporizing chamber; to provide improved regulating means for such apparatus; and to providev improved means for burning hydrocarbon fuel.
- FIG. 1 is a sectional view indicating the arrangement of the parts of the generating apparatus.
- FIG. 2 is a diagrammatic view, j showing the general arrangement of a complete system including the fuel combustion apparatus, motor and compressor, and illustrating a suitable arrangement of such parts.
- the power generator co-mprises a casing 1,having in its interior a dome-shaped battle wall 2 arranged to provide a vaporizing chamber 3 within it and an ignition space 4 communicating with an expansion space or combust-ion chamber 5 outside of the chamber 3.
- Concentric fuel and air inlet pipes, f designated 6 and 7 respectively in the drawings, extend axially into the chamber 3 and are controlled by valves 8 and 9 respectively.
- the bafl'le wall 2 at the point directly opposite the inner ends of the pipes 6 and 7 is provided with a conical projection 1Q located in axial alinement with said pipes, so that the fuel and air discharged from said pipes will be caused to spread and flow along the surface of the baiie wall 2 and become heated through contact therewith.
- annular series of narrow openings 11 connect the chamber 3 with the annular space 4 outside of the wall 2, which annular space forms the ignition chamber.
- This chamber is provided with a spark plug 12 or other suitable means for initially igniting the mixed fuel and air in the space 4.
- the passage 13,* which connects the ignition space 4 with the expansion space 5, is slightly contracted so as to retard the flow of gases through it and thereby encourage eddying and thorough mixing of the air and fuel in their passage through the ignition space 4.
- annular series of additional air inlets 14 enter the ignition space 4 from the jacket space 15 which surrounds the casing 1. These inlets 14 are preferably located adjacent to the inlets 11 and so directed that the currents of air and gas issuing from the two sets of inlets will co-nfiict and become thoroughly mixed.
- the combustion chamber 5 is of suiiicient volume to serve as a storage reservoir and allow a certain amount of expansion of the gases while the combustion which was started in the ignition space 4 is being completed.
- the outlet from the chamber 5 is preferably in the form of an expansion nozzle 16 of the De Laval type, whereby the pressure and temperature of the products of combustion are reduced, the energy being transformed into kinetic energy.
- a motor preferably in the form of an impulse turbine 17, is connected with the nozzle bustion discharged therefrom.
- the motor 19 driven by a motor 19, communicates by the pipe 2O with the jacket space 15, from which air is supplied to the air inlets of the combustion chamber.
- the motor 19 is shown independent of the motor 17 as it is preferred to have independent speed control.
- Fuel preferably liquid, is supplied to the pipe 6 by a pipe 21 controlled by the valve 8.
- An additional automatic valve 22 also controls the pipe 21.
- This valve in the form shown, is controlled by a lever 23 connected at its opposite end with a piston 24 movable in a small cylinder 25 and having one face exposed to the pressure of the gases in the chamber 5.
- a spring 26 normally urges the piston 24 to the position in which it is shown in Fig. 1, and also normally urges the opening of the valve 22.
- a fit- Y ting 28 is interposed in the air supply pipe crease so as to overcome the pressure ofthe spring 6, the piston 24 will move outward, causing the valve 22 to close and the piston 32 to cover the ports 31, so as to reduce or cut oif the .fuel and air supp1y,and if the excess of pressure exceeds a certain amount, predetermined by the strength of the spring 26, the piston will uncover an outlet opening 27 and cause a reduction of the pressure in the chamber 5. Normally, the outlet opening 27 will be covered, and thefmovement of the piston 24 will be slight, so as to automatically control the admission of fuel and air to correspond with the consumption of power by the motor.
- valve 9 should be so set that the mixture in the chamber 3 will be insuicient. to support mit complete combustion to take place in the ignition chamber 4. This combustion, together with the continued combustion in the chamber 5, heats the battle wall 2 to i the fuel inlets and i redness, and this is sucient to maintain the combustion after it is once started without requiring the continuous operation of the ignition device 12. striking the hot baille wall 2, becomes vaporized and thoroughly mixes with the air from the pipe 7 during its ,passage along the .wall 2. Y
- a power generator comprising a combustion chamber, means providing a closed baille wall in said chamber adapted Vto be The inflowing fuel, v
- a power generator comprising a combustion chamber having an lgnition space at one end and an expansion space at its other ⁇ end, and ahollow vaporizin chamber extending into said combustion c amber in position 'to vhave its walls heated by the products of combustion and havin a contracted opening communicating with said ignition space, and means for discharging air and fuel into said vaporizing chamber.
- a power generator comprising a combustion chamber having an ignition'space at one end and an expanslon space at its other end, and a hollow vaporizing chamber extending into said combustion chamber in ucts of combustion and having a contracted opening communicating with said ignition space, and means fo-r discharging air and fuel int-o said vaporizing chamber, said means being arranged to direct the inflowing fuel and air against the walls of said ignition chamber at a point distant from said contracted opening, and the adjacent part of the Wall of said ignition chamber being provided with a projection adapted to distribute the inflowing current of air and fuel and cause it to spread over the surface of said Wallin its contracted opening.
- a power generator comprising a combustion chamber having 4an ignition space at one end and an expansion space at its other end, and a hollow vaporizing chamber extending into said combustion chamber in position to have its walls lheated by the products of combustion and having a contracted opening communicatting with said ignition space, and means for discharging air and fuel into said vaporizing chamber, said combustion chamber having an additional air inlet communicating therewith, an air jacket surroundingsaid combustion chamber and communicating with said last passage toward said position to have its walls heated by the prodnamed air inlet opening and having an air baiie wall, a Huid actuated motor arranged to be driven bythe products of combustion from said combustion chamber, and means directly controlled by the pressure in said combustion chamber for regulating the admission of fuel thereto.
- a power generator comprising a combustion chamber having an ignition space at one end and an expansion space at its other end, and a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, and a fuel inlet valve controlling the admission of fuel to said vaporizing chamber and normally urged to an open position, and mechanism actuated by variations in the pressure in said combustion chamber and connected with said fuel inlet valve so as to tend to close the same through an increase in pressure in said combustion chamber.
- a power generator comprising a combustion chamber having an ignition space at one end and an expansion space at its other end, a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, a fuel inlet valve controlling the admission of fuel to said vaporizing chamber and normally urged to an open position, and mechanism actuated by variations in the pressure in said combustion chamber and adapted to control the admission of air to said combustion chamber.
- a power generator comprising a combustion chamber having an ignition space at one end and an expansion space at its other end, a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, a fuel inlet valve controlling the admission of fuel to said vaporizing chamber and normally urged to an open position, land mechanism actuated by variations in the pressure in said combustion chamber and adapted to control the admission of fuel and air to said combustion chamber.
- a power generator comprising a com'- bustion chamber having an ignition space at one end and an expansion space at its other end, a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a closed forward end and a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, and an air compressor driven by said motor and communicating with the air inlet.
- a power generator comprising a combustion chamber, means providing a baffle wall in said chamber adapted to be heated by the combustion of fuel in said chamber, said baiie wall having a deiecting portion, a fuel inlet nozzle in axial alinement with said dei'lecting portion arranged to direct the incoming, unconsumed fuel against said battle wall, a fluid actuated motor arranged to be driven by the products of combustion from said combustion chamber, and an eX- pansion nozzle interposed between said combustion chamber and said motor and adapted through expansion to reduce the temperature of the products of combustion in their passage to said motor.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Spray-Type Burners (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Description
J. lJANICKI. HYDROCARBON POWER GENERATOR.
APPLIUATION FILED A1112. 1911.
1,052,588. Patented Feb. 11,1913.
JOHN JANICKI, OF CHICAGO, ILLINOIS.
HYDROCARBN POWER-GENERATOR.
To all whom t may concern.'
Be it known that I, JOHN JANicKI, a citizen of the United States of America, and a resident of Chicago, county of Cook, State 5 of Illinois, have invented certain new and useful Improvements in Hydrocarbon Power-Generators, of which the following is a specification. Y
The main objects of this invention are to provide improved means for generating power from the combustion of hydrocarbon fuel and particularly adapted for utilizing the power due to expansion of the fuel during combustion, in such manner that the products of combustion may be used for operating a motor at comparatively low temperature; to provide in apparatus of this kind improved means for vapo-rizing liquid or powdered fuel; to provide improved means for preventing back firing in the vaporizing chamber; to provide improved regulating means for such apparatus; and to providev improved means for burning hydrocarbon fuel. 1
Al specific embodiment of this invention is illustrated in the accompanying drawing, in which- 4 *1 Figure 1 is a sectional view indicating the arrangement of the parts of the generating apparatus. Fig. 2 is a diagrammatic view, j showing the general arrangement of a complete system including the fuel combustion apparatus, motor and compressor, and illustrating a suitable arrangement of such parts.
In the construction shownl in the, drawings, the power generator co-mprises a casing 1,having in its interior a dome-shaped battle wall 2 arranged to provide a vaporizing chamber 3 within it and an ignition space 4 communicating with an expansion space or combust-ion chamber 5 outside of the chamber 3. Concentric fuel and air inlet pipes, f designated 6 and 7 respectively in the drawings, extend axially into the chamber 3 and are controlled by valves 8 and 9 respectively. The bafl'le wall 2 at the point directly opposite the inner ends of the pipes 6 and 7 is provided with a conical projection 1Q located in axial alinement with said pipes, so that the fuel and air discharged from said pipes will be caused to spread and flow along the surface of the baiie wall 2 and become heated through contact therewith.
At the end of the chamber 3 which is distant from the inner ends of the pipes 6 and Specication of Letters Patent.
Application filed April 12, 1911.
Patented Feb. 11, 1913.
Serial 110,620,610.
7, an annular series of narrow openings 11 connect the chamber 3 with the annular space 4 outside of the wall 2, which annular space forms the ignition chamber. This chamber is provided with a spark plug 12 or other suitable means for initially igniting the mixed fuel and air in the space 4. The passage 13,*which connects the ignition space 4 with the expansion space 5, is slightly contracted so as to retard the flow of gases through it and thereby encourage eddying and thorough mixing of the air and fuel in their passage through the ignition space 4.
'An annular series of additional air inlets 14 enter the ignition space 4 from the jacket space 15 which surrounds the casing 1. These inlets 14 are preferably located adjacent to the inlets 11 and so directed that the currents of air and gas issuing from the two sets of inlets will co-nfiict and become thoroughly mixed.
The combustion chamber 5 is of suiiicient volume to serve as a storage reservoir and allow a certain amount of expansion of the gases while the combustion which was started in the ignition space 4 is being completed. The outlet from the chamber 5 is preferably in the form of an expansion nozzle 16 of the De Laval type, whereby the pressure and temperature of the products of combustion are reduced, the energy being transformed into kinetic energy.
A motor, preferably in the form of an impulse turbine 17, is connected with the nozzle bustion discharged therefrom.
An air compressor 18, here shown, asv
driven by a motor 19, communicates by the pipe 2O with the jacket space 15, from which air is supplied to the air inlets of the combustion chamber. The motor 19 is shown independent of the motor 17 as it is preferred to have independent speed control.
Fuel, preferably liquid, is supplied to the pipe 6 by a pipe 21 controlled by the valve 8. An additional automatic valve 22 also controls the pipe 21. This valve, in the form shown, is controlled by a lever 23 connected at its opposite end with a piston 24 movable in a small cylinder 25 and having one face exposed to the pressure of the gases in the chamber 5. A spring 26 normally urges the piston 24 to the position in which it is shown in Fig. 1, and also normally urges the opening of the valve 22. A fit- Y ting 28 is interposed in the air supply pipe crease so as to overcome the pressure ofthe spring 6, the piston 24 will move outward, causing the valve 22 to close and the piston 32 to cover the ports 31, so as to reduce or cut oif the .fuel and air supp1y,and if the excess of pressure exceeds a certain amount, predetermined by the strength of the spring 26, the piston will uncover an outlet opening 27 and cause a reduction of the pressure in the chamber 5. Normally, the outlet opening 27 will be covered, and thefmovement of the piston 24 will be slight, so as to automatically control the admission of fuel and air to correspond with the consumption of power by the motor.
Accurate adjustment of the relative fuel and air admission maybe had by manipulating jthe valves 8 and 9. The valve 9 should be so set that the mixture in the chamber 3 will be insuicient. to support mit complete combustion to take place in the ignition chamber 4. This combustion, together with the continued combustion in the chamber 5, heats the battle wall 2 to i the fuel inlets and i redness, and this is sucient to maintain the combustion after it is once started without requiring the continuous operation of the ignition device 12. striking the hot baille wall 2, becomes vaporized and thoroughly mixes with the air from the pipe 7 during its ,passage along the .wall 2. Y
QIt will be seen that the arrangement of 'tion chambers is such that it is equally suitable for use in connection with liquid, gaseous, or powdered solid fuel, the only change required. for different fuels Vbeing such as can be lreadily made by those skilled in the art.
Although but one specific embodiment of this invention is herein shown and described, it will be understood that numerous details of the constructionfshown ma be altered or omitted'without departing from the spirit of this invention, as defined by thefollowing claims.
I claim 1. A power generator, comprising a combustion chamber, means providing a closed baille wall in said chamber adapted Vto be The inflowing fuel, v
heated by the combustion of fuel in said chamber, a fuel inlet nozzle arranged to direct the incoming, unconsumed fuel against saidclosed baffle wall, and a Huid actuated motor arranged to be driven by the products of combustion from said combustion chamber 2. `A power generator, comprising a combustion chamber having an lgnition space at one end and an expansion space at its other` end, and ahollow vaporizin chamber extending into said combustion c amber in position 'to vhave its walls heated by the products of combustion and havin a contracted opening communicating with said ignition space, and means for discharging air and fuel into said vaporizing chamber.
3. A power generator, comprising a combustion chamber having an ignition'space at one end and an expanslon space at its other end, and a hollow vaporizing chamber extending into said combustion chamber in ucts of combustion and having a contracted opening communicating with said ignition space, and means fo-r discharging air and fuel int-o said vaporizing chamber, said means being arranged to direct the inflowing fuel and air against the walls of said ignition chamber at a point distant from said contracted opening, and the adjacent part of the Wall of said ignition chamber being provided with a projection adapted to distribute the inflowing current of air and fuel and cause it to spread over the surface of said Wallin its contracted opening.
4. A power generator, comprising a combustion chamber having 4an ignition space at one end and an expansion space at its other end, and a hollow vaporizing chamber extending into said combustion chamber in position to have its walls lheated by the products of combustion and having a contracted opening communicatting with said ignition space, and means for discharging air and fuel into said vaporizing chamber, said combustion chamber having an additional air inlet communicating therewith, an air jacket surroundingsaid combustion chamber and communicating with said last passage toward said position to have its walls heated by the prodnamed air inlet opening and having an air baiie wall, a Huid actuated motor arranged to be driven bythe products of combustion from said combustion chamber, and means directly controlled by the pressure in said combustion chamber for regulating the admission of fuel thereto.
6. A power generator, comprising a combustion chamber having an ignition space at one end and an expansion space at its other end, and a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, and a fuel inlet valve controlling the admission of fuel to said vaporizing chamber and normally urged to an open position, and mechanism actuated by variations in the pressure in said combustion chamber and connected with said fuel inlet valve so as to tend to close the same through an increase in pressure in said combustion chamber.
7 A power generator, comprising a combustion chamber having an ignition space at one end and an expansion space at its other end, a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, a fuel inlet valve controlling the admission of fuel to said vaporizing chamber and normally urged to an open position, and mechanism actuated by variations in the pressure in said combustion chamber and adapted to control the admission of air to said combustion chamber.
8. A power generator, comprising a combustion chamber having an ignition space at one end and an expansion space at its other end, a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, a fuel inlet valve controlling the admission of fuel to said vaporizing chamber and normally urged to an open position, land mechanism actuated by variations in the pressure in said combustion chamber and adapted to control the admission of fuel and air to said combustion chamber.
9. A power generator, comprising a com'- bustion chamber having an ignition space at one end and an expansion space at its other end, a hollow vaporizing chamber extending into said combustion chamber in position to have its walls heated by the products of combustion and having a closed forward end and a contracted opening communicating with said ignition space, means for discharging air and fuel into said vaporizing chamber, and an air compressor driven by said motor and communicating with the air inlet.
10. A power generator, comprising a combustion chamber, means providing a baffle wall in said chamber adapted to be heated by the combustion of fuel in said chamber, said baiie wall having a deiecting portion, a fuel inlet nozzle in axial alinement with said dei'lecting portion arranged to direct the incoming, unconsumed fuel against said battle wall, a fluid actuated motor arranged to be driven by the products of combustion from said combustion chamber, and an eX- pansion nozzle interposed between said combustion chamber and said motor and adapted through expansion to reduce the temperature of the products of combustion in their passage to said motor.
Signed at Chicago this 6th day of April 1911.
JOHN JANICKI.
Witnesses EUGENE A. RUMMLER, MARY M. DELLMAN.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US62061011A US1052588A (en) | 1911-04-12 | 1911-04-12 | Hydrocarbon power-generator. |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US62061011A US1052588A (en) | 1911-04-12 | 1911-04-12 | Hydrocarbon power-generator. |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US1052588A true US1052588A (en) | 1913-02-11 |
Family
ID=3120849
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US62061011A Expired - Lifetime US1052588A (en) | 1911-04-12 | 1911-04-12 | Hydrocarbon power-generator. |
Country Status (1)
| Country | Link |
|---|---|
| US (1) | US1052588A (en) |
Cited By (45)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2493873A (en) * | 1945-04-25 | 1950-01-10 | Ingersoll Rand Co | Explosion gas turbine plant |
| US2570591A (en) * | 1947-04-26 | 1951-10-09 | Lockheed Aircraft Corp | Fuel control system for turbo power plants |
| US2570847A (en) * | 1949-01-29 | 1951-10-09 | Wright Aeronautical Corp | Air intake control apparatus for gas turbine power plants |
| US2611239A (en) * | 1949-03-18 | 1952-09-23 | Avco Mfg Corp | Fuel and combustion supporting medium control for turbine engine starters using excess fuel for cooling |
| US2613500A (en) * | 1945-06-22 | 1952-10-14 | Lysholm Alf | Gas turbine power plant having means for joint control of the fuel and the air supply |
| US2621477A (en) * | 1948-06-03 | 1952-12-16 | Power Jets Res & Dev Ltd | Combustion apparatus having valve controlled passages for preheating the fuel-air mixture |
| US2628474A (en) * | 1949-05-13 | 1953-02-17 | Floyd T Hague | Annular combustion liner having conical reentrant walls with fuel reversing elements |
| US2631426A (en) * | 1948-07-07 | 1953-03-17 | Curtiss Wright Corp | Engine starting turbine having combustion element supplied thereto in response to speed and combustion chamber pressure |
| US2632298A (en) * | 1947-08-15 | 1953-03-24 | United Aircraft Corp | Fuel control for turbine power plants |
| US2634804A (en) * | 1951-10-10 | 1953-04-14 | Henry L Erickson | Apparatus for generating heat |
| US2643511A (en) * | 1949-10-07 | 1953-06-30 | Avco Mfg Corp | Engine starter having combustion chamber supplied with fuel and combustion supporting medium for constant ratio by weight |
| US2655787A (en) * | 1949-11-21 | 1953-10-20 | United Aircraft Corp | Gas turbine combustion chamber with variable area primary air inlet |
| US2657527A (en) * | 1949-12-30 | 1953-11-03 | Philips Lab Inc | Hot-gas engine fuel control |
| US2657530A (en) * | 1947-11-21 | 1953-11-03 | Niles Bement Pond Co | Control apparatus for turbojet engines |
| US2668416A (en) * | 1946-09-28 | 1954-02-09 | Niles Bement Pond Co | Fuel control apparatus for turbojet engines |
| US2669838A (en) * | 1946-09-13 | 1954-02-23 | Niles Bement Pond Co | Fluid pump control apparatus for internal-combustion turbine engines |
| US2671314A (en) * | 1950-01-26 | 1954-03-09 | Socony Vacuum Oil Co Inc | Gas turbine and method of operation therefor |
| US2687273A (en) * | 1951-06-15 | 1954-08-24 | Gen Electric | Fuel regulating valve with fluidpressure servo responsive to ratio of two pressures |
| US2687009A (en) * | 1947-09-20 | 1954-08-24 | Niles Bement Pond Co | Control apparatus for resonant type jet engines |
| US2697482A (en) * | 1948-05-05 | 1954-12-21 | Foster Wheeler Corp | Apparatus for combustion of fluid fuel with oxygen |
| US2697327A (en) * | 1948-01-19 | 1954-12-21 | Bendix Aviat Corp | Fuel regulator for intermittent jet engines |
| US2718753A (en) * | 1951-01-02 | 1955-09-27 | Phillips Petroleum Co | Improved operation of internal combustion engine operating on liquid petroleum gas fuel |
| US2720753A (en) * | 1950-07-27 | 1955-10-18 | Power Jets Res & Dev Ltd | Combustion apparatus |
| US2736166A (en) * | 1956-02-28 | Afterburning and exhaust nozzle | ||
| US2738648A (en) * | 1949-06-14 | 1956-03-20 | Gen Electric | Liquid fuel control system for a rocket engine |
| US2779158A (en) * | 1951-06-26 | 1957-01-29 | Dungan Richard Thomas | Control for non-hypergolic liquid propellant rocket engines |
| US2816417A (en) * | 1952-08-13 | 1957-12-17 | Gen Electric | Control system for dual rotor pump drives |
| US2829494A (en) * | 1956-10-23 | 1958-04-08 | Willard L Christensen | Primary zone for gas turbine combustor |
| US2869321A (en) * | 1953-02-05 | 1959-01-20 | British Thomson Houston Co Ltd | Fuel reaction chambers |
| US2926492A (en) * | 1951-01-17 | 1960-03-01 | Bendix Aviat Corp | Self contained power plant using liquid decomposed into gaseous products |
| US2995008A (en) * | 1953-02-26 | 1961-08-08 | Phillips Petroleum Co | Fuel and oxidant control system and process for variable thrust rocket and jet engines |
| US3024596A (en) * | 1955-03-16 | 1962-03-13 | Strato Missiles Inc | Propulsion system with automatic control of fuel and air |
| US3062004A (en) * | 1959-05-18 | 1962-11-06 | United Aircraft Corp | Rocket motor starter |
| US3072189A (en) * | 1958-05-12 | 1963-01-08 | Phillips Petroleum Co | Process and apparatus for in situ combustion |
| US3088406A (en) * | 1959-06-22 | 1963-05-07 | Thompson Ramo Wooldridge Inc | Quantized impulse rocket |
| US3139726A (en) * | 1959-06-01 | 1964-07-07 | Shell Oil Co | Combustion with fluidization and after-burning |
| US4179879A (en) * | 1976-04-21 | 1979-12-25 | Kincaid Elmo Jr | Automatic steam pressure generator |
| US4538413A (en) * | 1982-11-19 | 1985-09-03 | Nissan Motor Company, Limited | Particle removing system for an internal combustion engine |
| US4604868A (en) * | 1982-12-04 | 1986-08-12 | Mazda Motor Corporation | Cleaner control for diesel engine exhaust gases |
| US4894005A (en) * | 1986-07-08 | 1990-01-16 | Bbc Brown Boveri Ag | Combustion chamber arrangement with a pre-combustion chamber for substoichiometric combustion |
| US4967562A (en) * | 1988-12-12 | 1990-11-06 | Sundstrand Corporation | Turbine engine with high efficiency fuel atomization |
| US4967563A (en) * | 1988-12-12 | 1990-11-06 | Sundstrand Corporation | Turbine engine with high efficiency fuel atomization |
| US4989404A (en) * | 1988-12-12 | 1991-02-05 | Sundstrand Corporation | Turbine engine with high efficiency fuel atomization |
| US5127822A (en) * | 1987-08-14 | 1992-07-07 | Toa Nenryo Kogyo Kabushiki Kaisha | Combustion apparatus with atomizer and method of controlling same |
| US20070137216A1 (en) * | 2005-12-20 | 2007-06-21 | General Electric Company | Gas turbine engine assembly and method of assembling same |
-
1911
- 1911-04-12 US US62061011A patent/US1052588A/en not_active Expired - Lifetime
Cited By (46)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2736166A (en) * | 1956-02-28 | Afterburning and exhaust nozzle | ||
| US2493873A (en) * | 1945-04-25 | 1950-01-10 | Ingersoll Rand Co | Explosion gas turbine plant |
| US2613500A (en) * | 1945-06-22 | 1952-10-14 | Lysholm Alf | Gas turbine power plant having means for joint control of the fuel and the air supply |
| US2669838A (en) * | 1946-09-13 | 1954-02-23 | Niles Bement Pond Co | Fluid pump control apparatus for internal-combustion turbine engines |
| US2668416A (en) * | 1946-09-28 | 1954-02-09 | Niles Bement Pond Co | Fuel control apparatus for turbojet engines |
| US2570591A (en) * | 1947-04-26 | 1951-10-09 | Lockheed Aircraft Corp | Fuel control system for turbo power plants |
| US2632298A (en) * | 1947-08-15 | 1953-03-24 | United Aircraft Corp | Fuel control for turbine power plants |
| US2687009A (en) * | 1947-09-20 | 1954-08-24 | Niles Bement Pond Co | Control apparatus for resonant type jet engines |
| US2657530A (en) * | 1947-11-21 | 1953-11-03 | Niles Bement Pond Co | Control apparatus for turbojet engines |
| US2697327A (en) * | 1948-01-19 | 1954-12-21 | Bendix Aviat Corp | Fuel regulator for intermittent jet engines |
| US2697482A (en) * | 1948-05-05 | 1954-12-21 | Foster Wheeler Corp | Apparatus for combustion of fluid fuel with oxygen |
| US2621477A (en) * | 1948-06-03 | 1952-12-16 | Power Jets Res & Dev Ltd | Combustion apparatus having valve controlled passages for preheating the fuel-air mixture |
| US2631426A (en) * | 1948-07-07 | 1953-03-17 | Curtiss Wright Corp | Engine starting turbine having combustion element supplied thereto in response to speed and combustion chamber pressure |
| US2570847A (en) * | 1949-01-29 | 1951-10-09 | Wright Aeronautical Corp | Air intake control apparatus for gas turbine power plants |
| US2611239A (en) * | 1949-03-18 | 1952-09-23 | Avco Mfg Corp | Fuel and combustion supporting medium control for turbine engine starters using excess fuel for cooling |
| US2628474A (en) * | 1949-05-13 | 1953-02-17 | Floyd T Hague | Annular combustion liner having conical reentrant walls with fuel reversing elements |
| US2738648A (en) * | 1949-06-14 | 1956-03-20 | Gen Electric | Liquid fuel control system for a rocket engine |
| US2643511A (en) * | 1949-10-07 | 1953-06-30 | Avco Mfg Corp | Engine starter having combustion chamber supplied with fuel and combustion supporting medium for constant ratio by weight |
| US2655787A (en) * | 1949-11-21 | 1953-10-20 | United Aircraft Corp | Gas turbine combustion chamber with variable area primary air inlet |
| US2657527A (en) * | 1949-12-30 | 1953-11-03 | Philips Lab Inc | Hot-gas engine fuel control |
| US2671314A (en) * | 1950-01-26 | 1954-03-09 | Socony Vacuum Oil Co Inc | Gas turbine and method of operation therefor |
| US2720753A (en) * | 1950-07-27 | 1955-10-18 | Power Jets Res & Dev Ltd | Combustion apparatus |
| US2718753A (en) * | 1951-01-02 | 1955-09-27 | Phillips Petroleum Co | Improved operation of internal combustion engine operating on liquid petroleum gas fuel |
| US2926492A (en) * | 1951-01-17 | 1960-03-01 | Bendix Aviat Corp | Self contained power plant using liquid decomposed into gaseous products |
| US2687273A (en) * | 1951-06-15 | 1954-08-24 | Gen Electric | Fuel regulating valve with fluidpressure servo responsive to ratio of two pressures |
| US2779158A (en) * | 1951-06-26 | 1957-01-29 | Dungan Richard Thomas | Control for non-hypergolic liquid propellant rocket engines |
| US2634804A (en) * | 1951-10-10 | 1953-04-14 | Henry L Erickson | Apparatus for generating heat |
| US2816417A (en) * | 1952-08-13 | 1957-12-17 | Gen Electric | Control system for dual rotor pump drives |
| US2869321A (en) * | 1953-02-05 | 1959-01-20 | British Thomson Houston Co Ltd | Fuel reaction chambers |
| US2995008A (en) * | 1953-02-26 | 1961-08-08 | Phillips Petroleum Co | Fuel and oxidant control system and process for variable thrust rocket and jet engines |
| US3024596A (en) * | 1955-03-16 | 1962-03-13 | Strato Missiles Inc | Propulsion system with automatic control of fuel and air |
| US2829494A (en) * | 1956-10-23 | 1958-04-08 | Willard L Christensen | Primary zone for gas turbine combustor |
| US3072189A (en) * | 1958-05-12 | 1963-01-08 | Phillips Petroleum Co | Process and apparatus for in situ combustion |
| US3062004A (en) * | 1959-05-18 | 1962-11-06 | United Aircraft Corp | Rocket motor starter |
| US3139726A (en) * | 1959-06-01 | 1964-07-07 | Shell Oil Co | Combustion with fluidization and after-burning |
| US3088406A (en) * | 1959-06-22 | 1963-05-07 | Thompson Ramo Wooldridge Inc | Quantized impulse rocket |
| US4179879A (en) * | 1976-04-21 | 1979-12-25 | Kincaid Elmo Jr | Automatic steam pressure generator |
| US4538413A (en) * | 1982-11-19 | 1985-09-03 | Nissan Motor Company, Limited | Particle removing system for an internal combustion engine |
| US4604868A (en) * | 1982-12-04 | 1986-08-12 | Mazda Motor Corporation | Cleaner control for diesel engine exhaust gases |
| US4894005A (en) * | 1986-07-08 | 1990-01-16 | Bbc Brown Boveri Ag | Combustion chamber arrangement with a pre-combustion chamber for substoichiometric combustion |
| US5127822A (en) * | 1987-08-14 | 1992-07-07 | Toa Nenryo Kogyo Kabushiki Kaisha | Combustion apparatus with atomizer and method of controlling same |
| US4967562A (en) * | 1988-12-12 | 1990-11-06 | Sundstrand Corporation | Turbine engine with high efficiency fuel atomization |
| US4967563A (en) * | 1988-12-12 | 1990-11-06 | Sundstrand Corporation | Turbine engine with high efficiency fuel atomization |
| US4989404A (en) * | 1988-12-12 | 1991-02-05 | Sundstrand Corporation | Turbine engine with high efficiency fuel atomization |
| US20070137216A1 (en) * | 2005-12-20 | 2007-06-21 | General Electric Company | Gas turbine engine assembly and method of assembling same |
| US8584464B2 (en) * | 2005-12-20 | 2013-11-19 | General Electric Company | Gas turbine engine assembly and method of assembling same |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US1052588A (en) | Hydrocarbon power-generator. | |
| US4013396A (en) | Fuel aerosolization apparatus and method | |
| US2363168A (en) | Heater | |
| US980801A (en) | Internal-combustion engine. | |
| US2482394A (en) | Gas turbine | |
| US1510688A (en) | Power plant | |
| US1236793A (en) | Power-generator. | |
| US3947230A (en) | Combustion chamber device with a rotary cup-shaped fuel-spreader | |
| US370251A (en) | Half to edward b | |
| US1345361A (en) | Heating apparatus | |
| US1349876A (en) | Apparatus for burning fuel | |
| US986308A (en) | Method and apparatus for generating motive power. | |
| US3485567A (en) | Liquid fuel burning appliance and components therefor | |
| US2267025A (en) | Pulverized fuel burner | |
| US1453669A (en) | Engine preheater | |
| US405219A (en) | Hydrocarbon-oil burner | |
| US1250160A (en) | Heating apparatus. | |
| US1337498A (en) | Starting device for burners | |
| US1166807A (en) | Furnace. | |
| US1602950A (en) | Oil burner | |
| US1355500A (en) | Burner | |
| US332313A (en) | Stephen wilcox | |
| US442793A (en) | bourne | |
| US753589A (en) | No model | |
| US738922A (en) | Vapor-burner. |