GB644719A - Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber - Google Patents
Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamberInfo
- Publication number
- GB644719A GB644719A GB13284/48A GB1328448A GB644719A GB 644719 A GB644719 A GB 644719A GB 13284/48 A GB13284/48 A GB 13284/48A GB 1328448 A GB1328448 A GB 1328448A GB 644719 A GB644719 A GB 644719A
- Authority
- GB
- United Kingdom
- Prior art keywords
- valve
- flame tube
- air
- sleeve
- casing
- 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
Links
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
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/20—Gas-turbine plants characterised by the use of combustion products as the working fluid using a special fuel, oxidant, or dilution fluid to generate the combustion products
- F02C3/30—Adding water, steam or other fluids for influencing combustion, e.g. to obtain cleaner exhaust gases
- F02C3/305—Increasing the power, speed, torque or efficiency of a gas turbine or the thrust of a turbojet engine by injecting or adding water, steam or other fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/26—Controlling the air flow
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
Abstract
644,719. Gas turbine plant. NAAMLOOZE VENNOOTSCHAP DE BATAAFSCHE PETROLEUM MAATSCHAPPIJ. May 14, 1948, No. 13284. Convention date, May 14, 1947. [Class 110(iii)] [Also in Group XII] To increase the output of a combustion chamber for a gas turbine plant of the kind in which an air stream is divided during normal operation into primary air which enters the combustion zone and secondary air which mixes with the combustion products leaving the combustion zone, means are provided to pass substantially the whole of said air stream into the combustion zone, to increase the fuel supply to the combustion zone and to add water or other volatile cooling,liquid in such quantity that the temperature of the mixture does not exceed that during normal operation. A combustion chamber for a jet propulsion gas turbine plant, Fig. 1, comprises an outer casing 4, a flame tube 5 and a fuel supply 12. A slide or sleeve valve 6 is arranged around the flame tube 5. In the normal position shown, Fig. 1, the air from the compressor 3 is divided, part flows into the combustion zone through passages near the burner and the remainder flows outside the flame tube to cool it and then passes through orifices 18 to mix with the combustion products. To increase the output of the combustion chamber the slide valve 6 is turned and the interconnecting pipes 24 which pass through helical slots 24<SP>1</SP> cause the valve to move rearwardly. This rearward movement of the valve shuts of the annular space between the flame tube 5 and casing 4 and all the air is forced to flow into the flame tube in the neighbourhood of the burner nozzle. Part of this air passes through orifices 14 which are shut off during normal operation by the ring 15 attached to the valve 6. The rotation of the valve 6 opens the orifices 6<SP>1</SP> and allows part of the combustion gases to pass to one or more jet pipes 9. A balancing piston 11 aids the rearward movement of the valve 6. Operation of the valve 6 is accompanied by an increase of the quantity of fuel supplied and the injection of water into the flame tube from pipes 19 and 20. A modification in which the air flows around the flame tube in the opposite direction to the flow of gases in the flame tube is described. In this arrangement the ports 18 are shut off by the rearward movement of the valve 6. In another modification, Fig. 9, a sleeve 25 is interposed between the flame tube 5 and casing 4. In normal operation, the annular space between this sleeve and the casing 4 is shut off by an annular valve 26 and the dilution air flows between the sleeve and flame tube 5 to the orifices 18. Rearward movement of the valve 6 opens the annular space between the sleeve 25 and casing 4, shuts off the annular space between the sleeve 25 and the flame tube 5 and closes the ports 18 causing part of the air to pass along the outside of the sleeve 25 and back along the outside of the flame tube to the inlet of the flame tube. The valve 6 may be actuated by a rod attached to the valve which engages a helical slot in the casing 4. The gases passing through the orifices 6<SP>1</SP> may actuate a turbine which is formed by the extension of the rotor and stator blades of the main turbine or a separate turbine surrounding the main turbine to the shaft of which it is attached by a one-way clutch. The main turbine may be in two parts, one of which drives an air compressor and the other an airscrew.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
NL644719X | 1947-05-14 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB644719A true GB644719A (en) | 1950-10-18 |
Family
ID=19791887
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB13284/48A Expired GB644719A (en) | 1947-05-14 | 1948-05-14 | Method of and apparatus for temporarily increasing the output of propulsive gases from a combustion chamber |
Country Status (1)
Country | Link |
---|---|
GB (1) | GB644719A (en) |
Cited By (11)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2847825A (en) * | 1953-07-31 | 1958-08-19 | Gen Motors Corp | Gas turbine thrust augmenter comprising water injection ring |
US2973624A (en) * | 1955-10-26 | 1961-03-07 | Gen Electric | Cowled dome liners |
US3038308A (en) * | 1956-07-16 | 1962-06-12 | Nancy W N Fuller | Gas turbine combustion chamber and method |
DE1153570B (en) * | 1959-04-17 | 1963-08-29 | Rolls Royce | Combustion device for gas turbine plants |
DE1197280B (en) * | 1960-02-25 | 1965-07-22 | Rolls Royce | Gas turbine engine with smoke control |
FR2572463A1 (en) * | 1984-10-30 | 1986-05-02 | Snecma | INJECTION SYSTEM WITH VARIABLE GEOMETRY. |
US4754600A (en) * | 1986-03-20 | 1988-07-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Axial-centripetal swirler injection apparatus |
WO2000011323A1 (en) * | 1998-08-21 | 2000-03-02 | Alliedsignal Inc. | Apparatus for water injection in a gas turbine combustor |
EP1207344A2 (en) * | 2000-11-17 | 2002-05-22 | Mitsubishi Heavy Industries, Ltd. | Combustor |
JP2016145669A (en) * | 2015-02-06 | 2016-08-12 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor, and steam injection gas turbine |
CN112412625A (en) * | 2019-08-23 | 2021-02-26 | 周维平 | Novel aircraft engine system designed based on gas pressure dynamics principle |
-
1948
- 1948-05-14 GB GB13284/48A patent/GB644719A/en not_active Expired
Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2847825A (en) * | 1953-07-31 | 1958-08-19 | Gen Motors Corp | Gas turbine thrust augmenter comprising water injection ring |
US2973624A (en) * | 1955-10-26 | 1961-03-07 | Gen Electric | Cowled dome liners |
US3038308A (en) * | 1956-07-16 | 1962-06-12 | Nancy W N Fuller | Gas turbine combustion chamber and method |
DE1153570B (en) * | 1959-04-17 | 1963-08-29 | Rolls Royce | Combustion device for gas turbine plants |
DE1197280B (en) * | 1960-02-25 | 1965-07-22 | Rolls Royce | Gas turbine engine with smoke control |
FR2572463A1 (en) * | 1984-10-30 | 1986-05-02 | Snecma | INJECTION SYSTEM WITH VARIABLE GEOMETRY. |
EP0182687A1 (en) * | 1984-10-30 | 1986-05-28 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation, "S.N.E.C.M.A." | Injection system with a variable geometry |
US4726182A (en) * | 1984-10-30 | 1988-02-23 | 501 Societe Nationale d'Etude et de Construction de Meteur d'Aviation-S.N.E.C.M.A. | Variable flow air-fuel mixing device for a turbojet engine |
US4754600A (en) * | 1986-03-20 | 1988-07-05 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation (Snecma) | Axial-centripetal swirler injection apparatus |
US6112511A (en) * | 1997-08-29 | 2000-09-05 | Alliedsignal, Inc. | Method and apparatus for water injection via primary jets |
WO2000011323A1 (en) * | 1998-08-21 | 2000-03-02 | Alliedsignal Inc. | Apparatus for water injection in a gas turbine combustor |
EP1207344A2 (en) * | 2000-11-17 | 2002-05-22 | Mitsubishi Heavy Industries, Ltd. | Combustor |
EP1207344A3 (en) * | 2000-11-17 | 2003-04-02 | Mitsubishi Heavy Industries, Ltd. | Combustor |
US6662547B2 (en) | 2000-11-17 | 2003-12-16 | Mitsubishi Heavy Industries, Ltd. | Combustor |
JP2016145669A (en) * | 2015-02-06 | 2016-08-12 | 三菱日立パワーシステムズ株式会社 | Gas turbine combustor, and steam injection gas turbine |
CN112412625A (en) * | 2019-08-23 | 2021-02-26 | 周维平 | Novel aircraft engine system designed based on gas pressure dynamics principle |
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