US3541790A - Hot gas generators - Google Patents

Hot gas generators Download PDF

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Publication number
US3541790A
US3541790A US764840A US3541790DA US3541790A US 3541790 A US3541790 A US 3541790A US 764840 A US764840 A US 764840A US 3541790D A US3541790D A US 3541790DA US 3541790 A US3541790 A US 3541790A
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Prior art keywords
turbine
compressor
combustion chamber
air
hot gas
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Expired - Lifetime
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US764840A
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Eric Kellett
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CAV Ltd
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CAV Ltd
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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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • 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
    • F02C3/34—Gas-turbine plants characterised by the use of combustion products as the working fluid with recycling of part of the working fluid, i.e. semi-closed cycles with combustion products in the closed part of the cycle
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air

Definitions

  • This invention relates to hot gas generators of the kind comprising in combination, a combustion chamber, a turbine which is driven by exhaust gases leaving the combustion chamber, a first compressor driven by said turbine for providing dilution air to the combustion chamber, and a second compressor for providing an air/fuel mixture to a burner disposed within the combustion chamber.
  • the object of this invention is to provide such an apparatus in a form in which the possibility of the generation of undesirable combustion products is minimised.
  • a portion of the exhaust gases leaving the turbine is admitted to the inlet of the second compressor thereby reducing the combustion temperature.
  • FIG. 1 is a sectional side elevation of one example of a hot gas generator to which the invention may be applied and FIG. 2 is a diagrammatic representation of the generator of FIG. 1 modified in accordance with the invention.
  • a body part 10 in which is mounted a rotary shaft 11.
  • a radial flow turbine rotor 12 At one end of the shaft is mounted a radial flow turbine rotor 12 which is accommodated within a turbine casing 13 having a tangential inlet 14 and an axially extending outlet 15.
  • the turbine casing is secured to the body part 10.
  • a pair of radial flow compressor rotors 16 and 17 disposed in compressor casings 18 and 19 respectively.
  • the compressor defined by the rotor 16 and casing is hereinafter called the first compressor whilst the compressor defined by the rotor 17 and the casing 19 is hereinafter called the second compressor.
  • the casings 18 and 19 have tangential outlets 20 and 21 respectively and inlets 22 and 23.
  • a combustion chamber indicated at 24 includes an outer casing 25 which is of generally cylindrical form and having a throat portion 26.
  • the downstream end of the combustion chamber is secured ted States Patent 0 to the inlet 14 of the turbine and upstream of the throat portion is an annular carrier 27 which serves to support the downstream end of a flame tube 28.
  • the upstream end of the flame tube is supported by a burner assembly 29 secured to the upstream end of the outer casing.
  • Surrounding the flame tube is an annular space to which dilution air is fed by the second compressor through a pipe 29.
  • Formed in the flame tube are holes 30 through which the dilution air flows into the flame tube.
  • the burner assembly 29 is in communication with the outlet 20 of the first compressor by way of a pipe 31.
  • an ignition plug 32 which extends into the flame tube downstream of the burner assembly 29 so as to ignite the air/fuel mixture entering the combustion chamber.
  • a carburettor indicated at 33 in FIG. 2 is provided.
  • the carburettor is supplied with fuel from a source 34 and when liquid fuel is employed a conventional fuel carburettor having a venturi may be provided in order to draw the fuel into the air stream.
  • a gaseous fuel such for instance as town gas, natural gas or vapourised petroleum gas
  • the gas will be supplied under a slight pressure to the nozzle of the carburettor so that the latter is little more than a mixing device for the air and gas.
  • the heated gases leaving the combustion chamber drive the turbine rotor prior to being discharged through ducting or the like.
  • the turbine rotor in turn drives the compressor rotors which supply the air/fuel mixture and the dilution air to the combustion chamber.
  • the dilution air acts to reduce the temperature of the gases entering the turbine so that the safe working temperature thereof is not exceeded.
  • the exhaust gases leaving the outlet of the turbine are admitted to the inlet 22 of the second compressor.
  • the exhaust gases leaving the turbine have a lower oxygen content than pure air and therefore the combustion temperature will be lowered.
  • the exhaust gases are conveyed along a duct 35 to a point downstream of the carburettor 33 and for controlling the quantity of gas flowing a valve 36 is provided. In this manner the combustion temperature can be controlled.
  • a hot gas generator comprising in combination, a combustion chamber, a burner disposed in the combustion chamber, a turbine which is driven by exhaust gases leaving the combustion chamber, a first compressor driven by said turbine for providing dilution air to the combustion chamber to control the temperature of the exhaust gases entering the turbine, a second compressor driven by the turbine for delivering an air/fuel mixture to the burner, a duct through which the exhaust gases can flow between the outlet of the turbine and the inlet of the second compressor and valve means for controlling the flow of gas through said duct, the exhaust gas when mixed with the air/fuel mixture supplied to the burner 4 acting to reduce the combustion temperature. of the.air/.. I FOREIGN PATENTS fuelmlxwre- 1,285,210 1/1962 France.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Sustainable Development (AREA)
  • Air Supply (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)

Description

Nov. 24, 1970 E. KELLETT 3,541,790
now GAS umnnm'rons Filed Oct. 5, 1968 2 Sheets-Shed 1 I I I I l I I I I I I I I I ATTORNEYS Nov. 24, '1970 a. KELLETT 3,541,790
now GAS umnxrons Filed Oct. 5, 1968 1 2 Sheets-Sheet 8 NTOR MW ATTORNEYS 3,541,790 HOT GAS GENERATORS Eric Kellett, Ealing, London, England, assignor to C.A.V. Limited Filed Oct. 3, 1968, Ser. No. 764,840 Claims priority, application Great Britain, Oct. 5, 1967, 45,458/ 67 Int. Cl. F02c 7/08 US. Cl. 60-3952 1 Claim ABSTRACT OF THE DISCLOSURE This invention relates to hot gas generators of the kind comprising in combination, a combustion chamber, a turbine which is driven by exhaust gases leaving the combustion chamber, a first compressor driven by said turbine for providing dilution air to the combustion chamber, and a second compressor for providing an air/fuel mixture to a burner disposed within the combustion chamber.
With such generators the exhaust gases leaving the turbine contain undesirable combustion products if the combustion temperature exceeds a certain value, and the object of this invention is to provide such an apparatus in a form in which the possibility of the generation of undesirable combustion products is minimised.
According to the invention in a generator of the kind specified, a portion of the exhaust gases leaving the turbine is admitted to the inlet of the second compressor thereby reducing the combustion temperature.
In the accompanying drawings:
FIG. 1 is a sectional side elevation of one example of a hot gas generator to which the invention may be applied and FIG. 2 is a diagrammatic representation of the generator of FIG. 1 modified in accordance with the invention.
Referring to the drawings there is provided a body part 10 in which is mounted a rotary shaft 11. At one end of the shaft is mounted a radial flow turbine rotor 12 which is accommodated within a turbine casing 13 having a tangential inlet 14 and an axially extending outlet 15. The turbine casing is secured to the body part 10. At the other end of the shaft is mounted a pair of radial flow compressor rotors 16 and 17 disposed in compressor casings 18 and 19 respectively. The compressor defined by the rotor 16 and casing is hereinafter called the first compressor whilst the compressor defined by the rotor 17 and the casing 19 is hereinafter called the second compressor. The casings 18 and 19 have tangential outlets 20 and 21 respectively and inlets 22 and 23.
Also provided is a combustion chamber indicated at 24 and this includes an outer casing 25 which is of generally cylindrical form and having a throat portion 26. The downstream end of the combustion chamber is secured ted States Patent 0 to the inlet 14 of the turbine and upstream of the throat portion is an annular carrier 27 which serves to support the downstream end of a flame tube 28. The upstream end of the flame tube is supported by a burner assembly 29 secured to the upstream end of the outer casing. Surrounding the flame tube is an annular space to which dilution air is fed by the second compressor through a pipe 29. Formed in the flame tube are holes 30 through which the dilution air flows into the flame tube. Furthermore, the burner assembly 29 is in communication with the outlet 20 of the first compressor by way of a pipe 31.
Also mounted on the casing 25 is an ignition plug 32 which extends into the flame tube downstream of the burner assembly 29 so as to ignite the air/fuel mixture entering the combustion chamber.
In order to entrain fuel with the air entering the first compressor a carburettor indicated at 33 in FIG. 2 is provided. The carburettor is supplied with fuel from a source 34 and when liquid fuel is employed a conventional fuel carburettor having a venturi may be provided in order to draw the fuel into the air stream. Where a gaseous fuel is used such for instance as town gas, natural gas or vapourised petroleum gas, the gas will be supplied under a slight pressure to the nozzle of the carburettor so that the latter is little more than a mixing device for the air and gas.
In operation the heated gases leaving the combustion chamber drive the turbine rotor prior to being discharged through ducting or the like. The turbine rotor in turn drives the compressor rotors which supply the air/fuel mixture and the dilution air to the combustion chamber. The dilution air acts to reduce the temperature of the gases entering the turbine so that the safe working temperature thereof is not exceeded.
With such an arrangement it has been found that the exhaust gases leaving the outlet 15 of the turbine can contain undesirable combustion products. This depends upon the type of fuel used but also upon the combustion temperature. It has been found that if the combustion temperature is increased then the degree of contamination also increases.
In order to limit the combustion temperature a portion of the exhaust gases leaving the outlet of the turbine are admitted to the inlet 22 of the second compressor. The exhaust gases leaving the turbine have a lower oxygen content than pure air and therefore the combustion temperature will be lowered. As shown in FIG. 2 the exhaust gases are conveyed along a duct 35 to a point downstream of the carburettor 33 and for controlling the quantity of gas flowing a valve 36 is provided. In this manner the combustion temperature can be controlled.
Having thus described my invention what I claim as new and desire to secure'by Letters Patent is:
1. A hot gas generator comprising in combination, a combustion chamber, a burner disposed in the combustion chamber, a turbine which is driven by exhaust gases leaving the combustion chamber, a first compressor driven by said turbine for providing dilution air to the combustion chamber to control the temperature of the exhaust gases entering the turbine, a second compressor driven by the turbine for delivering an air/fuel mixture to the burner, a duct through which the exhaust gases can flow between the outlet of the turbine and the inlet of the second compressor and valve means for controlling the flow of gas through said duct, the exhaust gas when mixed with the air/fuel mixture supplied to the burner 4 acting to reduce the combustion temperature. of the.air/.. I FOREIGN PATENTS fuelmlxwre- 1,285,210 1/1962 France.
References 1,103,687 3/1961 Germany. UNITED STATES PATENTS 256,077 7/1948 Switzerland.
2,358,815 9/1944 Lysholm 60-39.27 XR 5 2,595,505 5/1952 Bachle XR CARLTON R. CROYLE, Prlmary Examiner 2,616,252 11/1952 Robinson et a1. 6039.65 XR US. Cl. X.R. 2,633,698 4/1953 Nettel 6039.52 XR 6039.65
2,812,637 11/1957 Fox 60-3965 XR
US764840A 1967-10-05 1968-10-03 Hot gas generators Expired - Lifetime US3541790A (en)

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GB4545867 1967-10-05

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GB (1) GB1225759A (en)

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3703807A (en) * 1971-01-15 1972-11-28 Laval Turbine Combined gas-steam turbine power plant
US3785145A (en) * 1971-11-10 1974-01-15 Gen Motors Corp Gas turbine power plant
US3792581A (en) * 1970-12-22 1974-02-19 Nissan Motor System and method used in a gas turbine engine for minimizing nitrogen oxide emission
US3844113A (en) * 1972-11-02 1974-10-29 H Lockwood Friction impulse gas turbine
US3901026A (en) * 1973-11-05 1975-08-26 Gen Motors Corp Gas turbine with auxiliary gasifier engine
US4178754A (en) * 1976-07-19 1979-12-18 The Hydragon Corporation Throttleable turbine engine
US4204401A (en) * 1976-07-19 1980-05-27 The Hydragon Corporation Turbine engine with exhaust gas recirculation
US5586429A (en) * 1994-12-19 1996-12-24 Northern Research & Engineering Corporation Brayton cycle industrial air compressor
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
WO2004029432A2 (en) * 2002-09-26 2004-04-08 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US20050271500A1 (en) * 2002-09-26 2005-12-08 Ramgen Power Systems, Inc. Supersonic gas compressor
US20060021353A1 (en) * 2002-09-26 2006-02-02 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US20060034691A1 (en) * 2002-01-29 2006-02-16 Ramgen Power Systems, Inc. Supersonic compressor
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS6155319A (en) * 1984-08-28 1986-03-19 Mayekawa Mfg Co Ltd Power generating unit using displacement rotary air compressor
DE102008040060A1 (en) * 2008-07-01 2010-01-07 Webasto Ag Mobile, fuel-operated heater, particularly vehicle heater for cooling motor vehicle, particularly with switched off engine of motor vehicle, has conversion unit, particularly turbine

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2358815A (en) * 1935-03-28 1944-09-26 Jarvis C Marble Compressor apparatus
CH256077A (en) * 1942-02-26 1948-07-31 Jendrassik Georg Control process for gas turbine plants and equipment for carrying out the process.
US2595505A (en) * 1946-04-20 1952-05-06 Continental Aviat & Engineerin Coaxial combustion products generator, turbine, and compressor
US2616252A (en) * 1946-02-09 1952-11-04 Allis Chalmers Mfg Co Method of producing a gaseous motive fluid with pulverized fuel
US2633698A (en) * 1948-02-05 1953-04-07 Nettel Frederick Turbosupercharger means to heat intake of compression-ignition engine for starting
US2812637A (en) * 1951-12-21 1957-11-12 Phillips Petroleum Co Fuel air ratio regulation for combustion systems
DE1103687B (en) * 1959-06-30 1961-03-30 Siemens Ag Gas turbine plant
FR1285210A (en) * 1957-10-14 1962-02-23 Improvements to pressurized hot gas generators supercharged by a compressor, in particular by a turbo-compressor

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2358815A (en) * 1935-03-28 1944-09-26 Jarvis C Marble Compressor apparatus
CH256077A (en) * 1942-02-26 1948-07-31 Jendrassik Georg Control process for gas turbine plants and equipment for carrying out the process.
US2616252A (en) * 1946-02-09 1952-11-04 Allis Chalmers Mfg Co Method of producing a gaseous motive fluid with pulverized fuel
US2595505A (en) * 1946-04-20 1952-05-06 Continental Aviat & Engineerin Coaxial combustion products generator, turbine, and compressor
US2633698A (en) * 1948-02-05 1953-04-07 Nettel Frederick Turbosupercharger means to heat intake of compression-ignition engine for starting
US2812637A (en) * 1951-12-21 1957-11-12 Phillips Petroleum Co Fuel air ratio regulation for combustion systems
FR1285210A (en) * 1957-10-14 1962-02-23 Improvements to pressurized hot gas generators supercharged by a compressor, in particular by a turbo-compressor
DE1103687B (en) * 1959-06-30 1961-03-30 Siemens Ag Gas turbine plant

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3792581A (en) * 1970-12-22 1974-02-19 Nissan Motor System and method used in a gas turbine engine for minimizing nitrogen oxide emission
US3703807A (en) * 1971-01-15 1972-11-28 Laval Turbine Combined gas-steam turbine power plant
US3785145A (en) * 1971-11-10 1974-01-15 Gen Motors Corp Gas turbine power plant
US3844113A (en) * 1972-11-02 1974-10-29 H Lockwood Friction impulse gas turbine
US3901026A (en) * 1973-11-05 1975-08-26 Gen Motors Corp Gas turbine with auxiliary gasifier engine
US4178754A (en) * 1976-07-19 1979-12-18 The Hydragon Corporation Throttleable turbine engine
US4204401A (en) * 1976-07-19 1980-05-27 The Hydragon Corporation Turbine engine with exhaust gas recirculation
US5586429A (en) * 1994-12-19 1996-12-24 Northern Research & Engineering Corporation Brayton cycle industrial air compressor
US20030210980A1 (en) * 2002-01-29 2003-11-13 Ramgen Power Systems, Inc. Supersonic compressor
US20060034691A1 (en) * 2002-01-29 2006-02-16 Ramgen Power Systems, Inc. Supersonic compressor
US7334990B2 (en) 2002-01-29 2008-02-26 Ramgen Power Systems, Inc. Supersonic compressor
WO2004029432A2 (en) * 2002-09-26 2004-04-08 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
WO2004029432A3 (en) * 2002-09-26 2004-08-12 Ramgen Power Systems Inc Gas turbine power plant with supersonic gas compressor
US20040154305A1 (en) * 2002-09-26 2004-08-12 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US20050271500A1 (en) * 2002-09-26 2005-12-08 Ramgen Power Systems, Inc. Supersonic gas compressor
US20060021353A1 (en) * 2002-09-26 2006-02-02 Ramgen Power Systems, Inc. Gas turbine power plant with supersonic gas compressor
US7293955B2 (en) 2002-09-26 2007-11-13 Ramgen Power Systrms, Inc. Supersonic gas compressor
US7434400B2 (en) 2002-09-26 2008-10-14 Lawlor Shawn P Gas turbine power plant with supersonic shock compression ramps
US12066027B2 (en) 2022-08-11 2024-08-20 Next Gen Compression Llc Variable geometry supersonic compressor

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Publication number Publication date
GB1225759A (en) 1971-03-24
DE6800313U (en) 1971-03-11
FR1586958A (en) 1970-03-06
DE1800490A1 (en) 1969-06-04

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