US2404275A - Internal-combustion turbine plant - Google Patents
Internal-combustion turbine plant Download PDFInfo
- Publication number
- US2404275A US2404275A US492614A US49261443A US2404275A US 2404275 A US2404275 A US 2404275A US 492614 A US492614 A US 492614A US 49261443 A US49261443 A US 49261443A US 2404275 A US2404275 A US 2404275A
- Authority
- US
- United States
- Prior art keywords
- internal
- compressor
- turbine plant
- combustion
- combustion turbine
- 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
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/047—Heating to prevent icing
Definitions
- This invention relates to an intemal-combustion turbine plant.
- Our main object is to prevent the formation of ice in the compressor in a very simple way. Ice, it will be understood, is particularly liable to form in the compressor when such a plant is 7 being used to provide jet propulsion for an aircraft and the latter reaches a predetermined height above sea level.
- a further object is to provide means for abstracting a small quantitysay, 2%of the burning mixture, preferably before it passes to the turbine, and for injecting this small quantity into the air at the compressor inlet.
- the drawing shows a turbine plant having an axial-flow-type of rotary compressor comprising a stationary casing II with sets of fixed blades l2, l2 between and coacting with which are sets of blades l3, ii! on a rotary drum l4 keyed or otherwise secured upon a shaft 15.
- the plant has a plurality of combustion chambers l6, "5 which are arranged in parallel with one another and symmetrically spaced angularly round the axis of the shaft 15, and the delivery of air from the compressor outlet I1 is divided between these combustion chambers IS,
- the outlets l8 of the latter lead to an axial-flow-type of turbine including a stationary casing I9 carrying sets of fixed blades 20, 20 which coact with blades 2
- combustion chamber I6 Only the outline of a combustion chamber I6 is shown, as such combustion may take many known forms.
- the burner and fuel-injection arrangements form no part of the present invention and are not therefore illustrated.
- each combustion chamher It, near its outlet end, has an opening 23 leading to a valve chamber 24 which is shown as containing a poppet valve 25 pressed by a spring 26 to the closed position.
- Each poppet valve thus controls the delivery of some of the burning gases from the associated combustion chamber I B to a pipe 2'! leading from the valve chamber forwardly outside the compressor and curled round at its front end 28, such that some of the burning gases can be injected through the open ends 29 of these pipes into the air at d the compressor inlet 30.
- the open ends 29 of the pipes 21 are, it will be observed, symmetrically spaced angularly round the compressor inlet, so as to distribute evenly the injected gases.
- the interiors of the pipes 21 may, anywhere along their lengths, be interconnected to ensure uniform pressures therein.
- At 33 we show part of an annular pressure-equalizing pipe which interconnects the interiors of all the pipes 21.
- An internal-combustion turbine plant including an axial-flow-type of rotary compressor and a combustion chamber connected to the outletend of the compressor, in combination with a passage leading from the combustion chamber to the inlet end of the compressor, and controllable valve means which when opened allows about 2% of the burning mixture to be passed from the combustion chamber to the compressor inlet.
- An internal-combustion turbine plant including a compressor and a plurality of angularly-spaced combustion chambers arranged in parallel, and connected to the compressor outlet, in combination with means for abstracting a small quantity of the burning mixture from each combustion chamber and injecting it at angularly-spaced points into the air at the compressor inlet to raise the temperature thereof, and means for equalizing the delivery to said angularly-spaced points.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Description
July16,1946. T. CLARK ET- AL 2,404,215
INTERNAL-COMBUSTION TURBINE PLANT Filed June 28, 1943 Patented July 16, 1946 INTERNAL-COMBUSTION TURBINE PLANT Thomas Clark and William Henry Lindsey, Coventry, England, assignors to Armstrong Siddeley Motors Limited, Park Side, Coventry,
England Application June 28, 1943, Serial No. 492,614 In Great Britain October 2, 1942 3 Claims.
This invention relates to an intemal-combustion turbine plant.
Our main object is to prevent the formation of ice in the compressor in a very simple way. Ice, it will be understood, is particularly liable to form in the compressor when such a plant is 7 being used to provide jet propulsion for an aircraft and the latter reaches a predetermined height above sea level.
A further object is to provide means for abstracting a small quantitysay, 2%of the burning mixture, preferably before it passes to the turbine, and for injecting this small quantity into the air at the compressor inlet.
For a better understanding of these and other objects and advantages of the invention attention should be directed to the following description in which reference is made to the accompanying diagrammatic drawing. The single figure of this is a fragmentary sectional elevation of an internal-combustion turbine plant according to the invention.
The drawing shows a turbine plant having an axial-flow-type of rotary compressor comprising a stationary casing II with sets of fixed blades l2, l2 between and coacting with which are sets of blades l3, ii! on a rotary drum l4 keyed or otherwise secured upon a shaft 15. The plant has a plurality of combustion chambers l6, "5 which are arranged in parallel with one another and symmetrically spaced angularly round the axis of the shaft 15, and the delivery of air from the compressor outlet I1 is divided between these combustion chambers IS, The outlets l8 of the latter lead to an axial-flow-type of turbine including a stationary casing I9 carrying sets of fixed blades 20, 20 which coact with blades 2|, 2| on a rotor 22 keyed or otherwise secured upon and driving the shaft l5.
Only the outline of a combustion chamber I6 is shown, as such combustion may take many known forms. The burner and fuel-injection arrangements form no part of the present invention and are not therefore illustrated.
In the present instance each combustion chamher It, near its outlet end, has an opening 23 leading to a valve chamber 24 which is shown as containing a poppet valve 25 pressed by a spring 26 to the closed position. Each poppet valve thus controls the delivery of some of the burning gases from the associated combustion chamber I B to a pipe 2'! leading from the valve chamber forwardly outside the compressor and curled round at its front end 28, such that some of the burning gases can be injected through the open ends 29 of these pipes into the air at d the compressor inlet 30. We show, for control-- In practice it will be desirable for all the valves 25 to be operable in unison and by equal amounts, so that equal quantities of the burning gases will be abstracted from the different chambers l6. At the same time the open ends 29 of the pipes 21 are, it will be observed, symmetrically spaced angularly round the compressor inlet, so as to distribute evenly the injected gases. If desired the interiors of the pipes 21 may, anywhere along their lengths, be interconnected to ensure uniform pressures therein. At 33 we show part of an annular pressure-equalizing pipe which interconnects the interiors of all the pipes 21.
As stated, we contemplate abstracting, say, only 2% of the total burning gases, which, in ordinary conditions, will provide ample heat for deicing purposes.
vWhat we claim as our invention and desire to secure by Letters Patent of the United States is:
1. An internal-combustion turbine plant including an axial-flow-type of rotary compressor and a combustion chamber connected to the outletend of the compressor, in combination with a passage leading from the combustion chamber to the inlet end of the compressor, and controllable valve means which when opened allows about 2% of the burning mixture to be passed from the combustion chamber to the compressor inlet.
2. An internal-combustion turbine plant including a compressor and a plurality of angularly-spaced combustion chambers arranged in parallel, and connected to the compressor outlet, in combination with means for abstracting a small quantity of the burning mixture from each combustion chamber and injecting it at angularly-spaced points into the air at the compressor inlet to raise the temperature thereof, and means for equalizing the delivery to said angularly-spaced points.
3. In combination with an internal-combustion turbine plant including an air compressor, a plurality of combustion chambers arranged in parallel and connected to the compressor outlet and a turbine connected to the outlets of said combustion chambers, means providing passages for abstracting a small quantity of the hot gases produced in the combustion chambers and injecting said hot gases into the air at the compressor inlet to warm said air, and means for equalizing the pressure in said passages.
THOMAS CLARK. WILLIAM HENRY LINDSEY.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
GB2404275X | 1942-10-02 |
Publications (1)
Publication Number | Publication Date |
---|---|
US2404275A true US2404275A (en) | 1946-07-16 |
Family
ID=10905962
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US492614A Expired - Lifetime US2404275A (en) | 1942-10-02 | 1943-06-28 | Internal-combustion turbine plant |
Country Status (1)
Country | Link |
---|---|
US (1) | US2404275A (en) |
Cited By (28)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2482720A (en) * | 1947-01-13 | 1949-09-20 | Napier & Son Ltd | Prevention of ice formation in air intakes on aircraft and other fast-moving vehicles |
US2557131A (en) * | 1948-02-20 | 1951-06-19 | Charles H Miller | Gas turbine and cycle |
US2572346A (en) * | 1948-05-25 | 1951-10-23 | Rolls Royce | Abstracting hot gas from the exhausts of gas-turbine engines |
US2599470A (en) * | 1947-10-22 | 1952-06-03 | Bbc Brown Boveri & Cie | Axial flow compressor, particularly for combustion gas turbine plants |
US2625010A (en) * | 1947-04-02 | 1953-01-13 | Armstrong Siddeley Motors Ltd | Means for preventing internal-combustion turbine units from icing |
US2625794A (en) * | 1946-02-25 | 1953-01-20 | Packard Motor Car Co | Gas turbine power plant with diverse combustion and diluent air paths |
US2630965A (en) * | 1947-06-20 | 1953-03-10 | Rolls Royce | Device for reducing or preventing ice formation on compressors of gas-turbine engines |
US2633698A (en) * | 1948-02-05 | 1953-04-07 | Nettel Frederick | Turbosupercharger means to heat intake of compression-ignition engine for starting |
US2634049A (en) * | 1947-10-09 | 1953-04-07 | Westinghouse Electric Corp | Anti-icing means for the air intake of gas turbines |
US2634581A (en) * | 1947-08-27 | 1953-04-14 | Rolls Royce | Separate burner system for deicing the inlets of multiple gas turbine units |
US2636666A (en) * | 1947-08-20 | 1953-04-28 | Rolls Royce | Gas turbine engine with de-icing apparatus |
US2645080A (en) * | 1949-10-25 | 1953-07-14 | United Aircraft Corp | Deicer for jet engines |
US2647366A (en) * | 1946-06-24 | 1953-08-04 | William J Mccann | Means for preventing ice formation in jet propulsion and gas turbine engines |
US2648193A (en) * | 1951-04-10 | 1953-08-11 | Westinghouse Electric Corp | Anti-icing apparatus having means to control temperature and pressure of the heating gases |
US2654992A (en) * | 1947-03-18 | 1953-10-13 | Bristol Aeroplane Co Ltd | Apparatus for preventing or reducing the formation of ice on the air ducts of gas turbine engines |
US2663993A (en) * | 1945-10-10 | 1953-12-29 | Westinghouse Electric Corp | Deicing apparatus |
US2668596A (en) * | 1947-07-04 | 1954-02-09 | Rotol Ltd | Anthcing and intake means for turbine-propeller units |
US2669092A (en) * | 1953-02-03 | 1954-02-16 | Nils W Hammaren | Gas turbine power plant with exhaust gas recycling |
US2702665A (en) * | 1951-03-07 | 1955-02-22 | United Aircraft Corp | Stator construction for axial flow compressors |
US2705866A (en) * | 1951-06-28 | 1955-04-12 | Holley Carburetor Co | De-icing for gas turbines |
US2744992A (en) * | 1951-03-30 | 1956-05-08 | Gen Motors Corp | Deicing control |
US2864236A (en) * | 1952-06-05 | 1958-12-16 | Snecma | Method of and means for the control of the air inlet opening of a jet propulsion unit or a gas turbine engine |
US3029011A (en) * | 1955-10-13 | 1962-04-10 | Bristol Siddeley Engines Ltd | Rotary compressors or turbines |
US3342406A (en) * | 1964-06-23 | 1967-09-19 | Bbc Brown Boveri & Cie | Method for preventing damage by corrosion of the adjustable mechanism of guide blading of turbomachines and turbomachine with corrosion prevention device |
US3410093A (en) * | 1967-05-26 | 1968-11-12 | Ghougasian John Nazareth | Reaction thrust engine with fluid operated compressor |
DE2726522A1 (en) * | 1976-06-14 | 1977-12-29 | Gen Electric | GAS TURBINE ENGINE AND METHOD OF OPERATING THE SAME |
US6412284B1 (en) * | 2001-03-07 | 2002-07-02 | General Electric Company | Methods and apparatus for supplying air to gas turbine engines |
US6742339B2 (en) | 2002-09-06 | 2004-06-01 | General Electric Company | Methods and apparatus for exhausting gases from gas turbine engines |
-
1943
- 1943-06-28 US US492614A patent/US2404275A/en not_active Expired - Lifetime
Cited By (29)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US2663993A (en) * | 1945-10-10 | 1953-12-29 | Westinghouse Electric Corp | Deicing apparatus |
US2625794A (en) * | 1946-02-25 | 1953-01-20 | Packard Motor Car Co | Gas turbine power plant with diverse combustion and diluent air paths |
US2647366A (en) * | 1946-06-24 | 1953-08-04 | William J Mccann | Means for preventing ice formation in jet propulsion and gas turbine engines |
US2482720A (en) * | 1947-01-13 | 1949-09-20 | Napier & Son Ltd | Prevention of ice formation in air intakes on aircraft and other fast-moving vehicles |
US2654992A (en) * | 1947-03-18 | 1953-10-13 | Bristol Aeroplane Co Ltd | Apparatus for preventing or reducing the formation of ice on the air ducts of gas turbine engines |
US2625010A (en) * | 1947-04-02 | 1953-01-13 | Armstrong Siddeley Motors Ltd | Means for preventing internal-combustion turbine units from icing |
US2630965A (en) * | 1947-06-20 | 1953-03-10 | Rolls Royce | Device for reducing or preventing ice formation on compressors of gas-turbine engines |
US2668596A (en) * | 1947-07-04 | 1954-02-09 | Rotol Ltd | Anthcing and intake means for turbine-propeller units |
US2636666A (en) * | 1947-08-20 | 1953-04-28 | Rolls Royce | Gas turbine engine with de-icing apparatus |
US2634581A (en) * | 1947-08-27 | 1953-04-14 | Rolls Royce | Separate burner system for deicing the inlets of multiple gas turbine units |
US2634049A (en) * | 1947-10-09 | 1953-04-07 | Westinghouse Electric Corp | Anti-icing means for the air intake of gas turbines |
US2599470A (en) * | 1947-10-22 | 1952-06-03 | Bbc Brown Boveri & Cie | Axial flow compressor, particularly for combustion gas turbine plants |
US2633698A (en) * | 1948-02-05 | 1953-04-07 | Nettel Frederick | Turbosupercharger means to heat intake of compression-ignition engine for starting |
US2557131A (en) * | 1948-02-20 | 1951-06-19 | Charles H Miller | Gas turbine and cycle |
US2572346A (en) * | 1948-05-25 | 1951-10-23 | Rolls Royce | Abstracting hot gas from the exhausts of gas-turbine engines |
US2645080A (en) * | 1949-10-25 | 1953-07-14 | United Aircraft Corp | Deicer for jet engines |
US2702665A (en) * | 1951-03-07 | 1955-02-22 | United Aircraft Corp | Stator construction for axial flow compressors |
US2744992A (en) * | 1951-03-30 | 1956-05-08 | Gen Motors Corp | Deicing control |
US2648193A (en) * | 1951-04-10 | 1953-08-11 | Westinghouse Electric Corp | Anti-icing apparatus having means to control temperature and pressure of the heating gases |
US2705866A (en) * | 1951-06-28 | 1955-04-12 | Holley Carburetor Co | De-icing for gas turbines |
US2864236A (en) * | 1952-06-05 | 1958-12-16 | Snecma | Method of and means for the control of the air inlet opening of a jet propulsion unit or a gas turbine engine |
US2669092A (en) * | 1953-02-03 | 1954-02-16 | Nils W Hammaren | Gas turbine power plant with exhaust gas recycling |
US3029011A (en) * | 1955-10-13 | 1962-04-10 | Bristol Siddeley Engines Ltd | Rotary compressors or turbines |
US3342406A (en) * | 1964-06-23 | 1967-09-19 | Bbc Brown Boveri & Cie | Method for preventing damage by corrosion of the adjustable mechanism of guide blading of turbomachines and turbomachine with corrosion prevention device |
US3410093A (en) * | 1967-05-26 | 1968-11-12 | Ghougasian John Nazareth | Reaction thrust engine with fluid operated compressor |
DE2726522A1 (en) * | 1976-06-14 | 1977-12-29 | Gen Electric | GAS TURBINE ENGINE AND METHOD OF OPERATING THE SAME |
US4083181A (en) * | 1976-06-14 | 1978-04-11 | The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration | Gas turbine engine with recirculating bleed |
US6412284B1 (en) * | 2001-03-07 | 2002-07-02 | General Electric Company | Methods and apparatus for supplying air to gas turbine engines |
US6742339B2 (en) | 2002-09-06 | 2004-06-01 | General Electric Company | Methods and apparatus for exhausting gases from gas turbine engines |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US2404275A (en) | Internal-combustion turbine plant | |
US2566373A (en) | Fuel control system for turbojet engines | |
US2672726A (en) | Ducted fan jet aircraft engine | |
US3048014A (en) | Combustion chamber for jets and similar engines | |
US3877219A (en) | Constant volume combustion gas turbine with intermittent flows | |
US2579321A (en) | Apparatus for producing gas under pressure | |
US2858672A (en) | Monofuel decomposition apparatus | |
US2653446A (en) | Compressor and fuel control system for high-pressure gas turbine power plants | |
RU2674172C1 (en) | Turbo engine and method for operation thereof | |
US2469679A (en) | Gas turbine | |
US3119436A (en) | Furnace for intermittent combustion, particulary for steam boilers and heating boilers | |
US2486967A (en) | Airplane wing with jet propulsion apparatus | |
US2625010A (en) | Means for preventing internal-combustion turbine units from icing | |
US2629225A (en) | Pulse flow fuel injection system for turbojet engines | |
US2694899A (en) | Liquid fuel vaporizing apparatus | |
US3073114A (en) | Vortex venturi | |
US1346509A (en) | Explosion gas-turbine | |
US2755621A (en) | Gas turbine installations with output turbine by-pass matching the output turbine pressure drop | |
US2096184A (en) | Power plant | |
US2312605A (en) | Gas turbine plant | |
US2296023A (en) | Burner | |
US1174439A (en) | Gas-turbine. | |
US3204404A (en) | Double flow jet-engines | |
US2989849A (en) | Fuel control system for a twin spool gas turbine power plant | |
US2708340A (en) | Gas control in afterburner |