US3650106A - Combustion chamber for gas turbine - Google Patents

Combustion chamber for gas turbine Download PDF

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Publication number
US3650106A
US3650106A US865273A US3650106DA US3650106A US 3650106 A US3650106 A US 3650106A US 865273 A US865273 A US 865273A US 3650106D A US3650106D A US 3650106DA US 3650106 A US3650106 A US 3650106A
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United States
Prior art keywords
air
inner casing
slots
combustion chamber
downstream
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Expired - Lifetime
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US865273A
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English (en)
Inventor
Jack Guillot
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Bennes Marrel SA
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Bennes Marrel SA
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    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/46—Combustion chambers comprising an annular arrangement of several essentially tubular flame tubes within a common annular casing or within individual casings
    • F23R3/48—Flame tube interconnectors, e.g. cross-over tubes
    • 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
    • F02C7/22—Fuel supply systems
    • 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
    • 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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/54—Reverse-flow combustion chambers

Definitions

  • ABSTRACT Combustion chamber for a gas turbine comprising two concentric sheet metal casings where the air enters and the compressed gases circulate in contra-current, chiefly notable in that the exterior casing, open at one end to receive the air, is closed at the other end by a cap provided with radial ribs which surround a central jet provided to inject an atomized combustible liquid, this jet .opening onto one extremity of the interior casing where it is surrounded by profiled blades fixed slantwise to rotate the air, while this inner casing defines an expanded zone provided with a large number of small slots for the admission of the primary air of combustion, this expanded zone being extended by a short convergent part into which open lateral slots of relatively large diameter for the admission of second air after which the inner casing is continued up to the escape extremity by a divergent zone having wide lateral slots for the admission of coolant air, these slots being surrounded by
  • This combustion chamber can, moreover, show the following characteristics envisaged separately or in combination:
  • Lateral slots for the secondary air are each provided with a tubular portion which is inclined towards the jet in the direction of the general axis of the chamber.
  • the present invention relates to an improved combustion chamber for a gas turbine.
  • the present invention has for its object to provide a combustion chamber capable of increasing the thermal efficiency of a gas turbine, this combustion chamber being usable with a range of such turbines.
  • a combustion chamber for a gas turbine comprises two concentric sheet metal casings in which the intake air and the compressed gases pass in contraflow.
  • the exterior casing is open at one end to receive the intake air and is terminated at the other end by an upper cap provided with radial ribs which surround a central jet injecting an atomized combustible liquid, this jet opening into one extremity of the interior casing where it is surrounded by profiled blades fixed slantwise to rotate the air.
  • This interior casing has an expanded zone provided with a large number of small holes for the admission of the primary air of combustion, this expanded zone being extended by a short convergent part having relatively large diameter lateral slots with tubes for the admission of secondary air, after which the internal casing is continued to its exhaust extremity by a divergent zone having wide lateral slots for the admission of coolant air. These slots are surrounded by an air deflector fixed on the extremity of the internal shell.
  • an odd number of secondary air ports and a number, also odd, of slots for the admission of coolant air is provided. This prevents the formation of directly opposed air currents.
  • two combustion chambers are mounted parallel to one another, the equal action thereof being assured by a bypass channel connecting the combustion zones of the two internal casings.
  • the two combustion chambers are disposed in the same transverse plane with respect to the main axis of the turbine, and they both connect with a common chamber surrounding the axis of the rotors, from whence the gas flows out axially through the fixed blades'ofa deflector to the high pressure rotor.
  • each combustion chamber is provided with a retractable sparking plug.
  • This spark plug may be placed on a face of the expanded zone of the interior casing.
  • a return spring maintains the spark plug outwards (i.e., extended into the zone) when the turbine is at rest, the pressure in the zone automatically retracting this spark plug as soon as the turbine begins to rotate.
  • This retracting pressure is preferably made that ofthe compressor.
  • the jet is fed, through a valve controlled by an electromagnet coil, this valve controlling the direction, either towards the jet, or towards a return channel, of the fuel which it receives from a channel constantly maintained under pressure.
  • This device prevents the formation of air traps upstream of the jet during the starting-up of the machine and the ignition of the fuel in the combustion chamber.
  • the valve retains its position as soon as the chamber is fed with fuel, irrespective of the rate of the machine.
  • FIG. 1 is a fragmentary view showing the position of two combustion chambers according to the invention, located on the body ofa gas turbine,
  • FIG. 2 is a partial section along the line II-II ofFIG. 4,
  • FIG. 3 is an axial section along the line IIIIIl of FIG. 6 showing the arrangement of a retractable plug
  • FIG. 4 is a transverse section of the turbine taken along the line IVIV ofFIG. 1,
  • FIG. 5 shows on an enlarged scale the injector shown in FIGS. 2 and 3,
  • FIG. 6 is a partial section taken along the line VI-Vl of FIG. 3.
  • FIG. 1 shows a part of a gas turbine which, forms part of a gas turbine prime mover.
  • This device comprises chiefly those parts shown very schematically in FIG. 1, namely a rotor 2 of a centrifugal compressor, two combustion chambers 3 and a rotor of a high pressure turbine 4.
  • the compressor 2 blows air into the chambers 3 from whence the hot gases emerge under pressure to cause rotation of the high pressure rotor 4.
  • the turbine may comprise various known elements, such as one or more deflectors and low pressure rotors.
  • Each combustion chamber 3 comprises two concentric sheet iron casings, an outer casing 7 and an inner casing 8 (FIG; 4).
  • Each outer casing 7 is fixed directly on a housing 9 surrounding the shaft 6 of the turbine, this housing comprising an annular collector 10 receiving the air from the compressor 2.
  • the outer casing 7 is closed at its apex by a truncated cap 11 on which is fixed a fuel injector 12.
  • This injector comprises a jet 13 which will be described later.
  • An interior sheet iron casing 8 has an apex l4 surrounding the jet 13 of the fuel injector. Downstream of the apex 14, the casing comprises a truncated cone 15, then an expanded cylindrical main combustion zone 16 and a convergent truncated cone l7 beyond which it is extended by a long divergent portion 18. This part terminates in a cylindrical coupling 19 which links up the combustion chamber with a collector 20 which directs the heated gas concentrically around the shaft 6, into a high pressure deflector 21.
  • FIGS. 2 and 3 show the shape of the inner casing 8, of which details are shown in FIG. 4.
  • the apex 14 of the inner casing 8 comprises fixed profiled blades 22 which are disposed around the jet 13, in such a way as to form a vortex from the passing air.
  • radial ribs 24 are spaced equidistantly around the apex l4 and fixed to the cone 11 and to the shell 7 of the exterior casing.
  • the divergent portion 15 is bored with two series of small diameter holes 25. If the total diameter 26 of the combustion chamber 3 is of the order of millimeters, the divergent portion 15 is bored with two series of holes, each series comprising 12 holes each having a diameter of3 millimeters.
  • the zone 16 has bored therein a large number of small holes.
  • the expanded zone 16 has two series 27 of holes, each series containing 32 holes each of a diameter of 4 millimeters and being located on each side of a central series 28 made of 16 holes of a diameter of 4 millimeters.
  • the convergent portion 17 has an odd number of wide holes in each of which there is soldered a tubular length of pipe 29, the inner ends of which are tilted towards the top of the chamber 3. There are seven such tubes, each of a diameter of the order of 4 millimeters, spaced around the axis 30 of the chamber.
  • the divergent zone At its extremity, immediately in front of the cylindrical coupling 19, the divergent zone has large slots 32 distributed around the axis 30. These slots 32 are preferably odd in number, so as not to provide exactly opposed gas flows. These slots are seven in number and each has a width 33 of about 20 millimeters, and a height of 34 of 50 millimeters.
  • the expanded zones 16 of the internal casings 8 are connected by means of a cross-connecting channel 36 provided at its center with an expansion bellows 37.
  • FIG. shows the details of an injector 12 for a combustion chamber.
  • This injector comprises a coil 38 of an electromagnet actuating a poppet valve 39.
  • the valve 39 is located on a fixed seat 40 which it seals, preventing the jet 13 from receiving fuel under pressure from a feed channel 41.
  • This fuel circulates through longitudinal channels 42 in the shell of the valve 39, and escapes by a return channel 43 (Arrow 44).
  • valve 39 When the coil is energized, the valve 39 rises and comes to rest with its apex on a fixed seat 45, uncovering the seat 40. In consequence, the return channel 43 is blocked, and the jet 13 is fed with fuel from the channel 41.
  • valve 39 is either open or closed.
  • the regulation of the rate of injection of the fuel into the chamber 3 by the jet 13 is effected by the control and regulating means of the turbine (not shown).
  • a support cylinder 46 of a retractable sparking plug 47 is fixed to the external casing 7.
  • the plug When the plug is in the working position 47a (FIG. 6) it extends into the inner casing 8 at the level of the expanded zone 16.
  • This sparking plug comprises two electrodes (not shown), between which it is possible to produce a series of high tension electrical sparks.
  • the spark plug 47 is integral with a piston 48 which slides in the interior of the support cylinder 46.
  • This cylinder is divided into two chambers of which one contains a return spring 49 tending to extend the plug into the position 470; the other chamber 50 communicates with the interior of the combustion chamber.
  • the pressure prevailing in the combustion chamber is sufficient to push the plug back into the retracted position 4717.
  • the pressure supplied by the compressor 2 is equal to that in the chamber 50 and, the spring 49 keeps the spark plug in the working position 47a.
  • the pressure in the combustion chamber increases.
  • the plug is sparked to ignite the injected fuel, whereafter the pressure in the combustion chamber rises until the turbine is at full load.
  • the pressure increase retracts the plug, which thereafter remains so, as long as combustion contmues.
  • the operation of the combustion chamber 3 is as follows:
  • the air issuing from the collector l0 circulates between the casings 7 and 8 as indicated by the arrows 51 (FIG. 4).
  • the deflector 35 prevents the air from impinging directly on the seven slots 32. Having reached the region of the cap 11, the current of air changes direction (Arrows 23) and passes into the vortex 22 where it is set in rotation to assist the atomization ofthe fuel provided by the jet 13. At this point, an amount of primary air which has penetrated into the inner casing 8 through the series of small holes 25, 27 and 28 is added thereto.
  • the large tubed apertures provide a secondary air to complete the homogenation and burning of the mixture of air and fuel.
  • the return of the secondary air (Arrows 54) is assisted by the tilt of the tubes 29.
  • the primary air mixed with the fuel at the levels of the expanded zone 16 and the convergent zone 17, is the minimum quantity of air necessary to completely burn the fuel.
  • the spent gases advance into the divergent zone 18 (Arrows 52) in contra-flow to the peripheral air (Arrows 51).
  • the spent gases receive a portion of coolant air with which they are mixed (Arrows 53).
  • the temperature of the mixture being thus brought to a desired level, the spent gas is'discharged into the collector 20 to activate the high pressure rotor 4 of the turbine.
  • a combustion chamber for a gas turbine comprising inner and outer concentric casings wherein the inlet air travels in one direction within the inner casing, said outer casing being closed at one end with a plurality of radially extending ribs secured internally thereof and surrounding the corresponding end of said inner casing, fuel injection means secured in the closed end of said outer casing and disposed concentrically with respect to said inner and outer casings, said inner casing defining an annular opening about said fuel injection means, blade means disposed in said annular opening to form a vortex from the passing air, an expansion chamber formed by said inner casing downstream from said blade means and having a diameter larger than the diameter of said annular opening, a plurality of primary and secondary air openings formed through said expansion chamber, said inner casing diverging outwardly downstream from said expansion chamber, cooling slots extending through the diverging portion of said inner casing, and annular deflector means secured to said diverging portion downstream of said slots and substantially overlying said slots in spaced relation intermediate said casings to prevent the direct
  • a combustion chamber as set forth in claim 1 further comprising additional air opening means formed in said diverging portion immediately downstream of said secondary air inlet openings which are smaller than said secondary air inlet openings.
  • cooling air slots are disposed downstream of said additional air openings, said cooling slots being odd in number and disposed circumferentially about said diverging portion.
  • annular deflector means has a truncated conical configuration with the smaller diameter portion being secured to said diverging portion of said inner casing downstream of said cooling slots.
  • a combustion chamber as set forth in claim 1 further comprising retractable spark plug means movable between a working position wherein said plug means extends into the inner casing and a retracted position wherein said plug means does not extend into said inner casing, spring means normally biasing said plug means into said working position and piston means responsive to increased pressures for retracting said plug means during self-sustained operation of the gas turbine.
  • a gas turbine engine of the type having a compressor means, turbine means, and a pair of combustion chambers intermediate said compressor means and said turbine means, the improvement comprising inner and outer concentric casings wherein the inlet air travels in one direction between said casings and said outlet gases travel in the opposite direction within the inner casing, said outer casing being closed at one end with a plurality of radially extending ribs secured internally thereof and surrounding the corresponding end of said inner casing, fuel injection means secured in the closed end of pansion chamber, said inner casing diverging outwardly downstream from said expansion chamber, cooling slots extending through the diverging portion of said inner casing, and annular deflector means secured to said diverging portion downstream of said slots and substantially overlying said slots in spaced relation intermediate said casings to prevent the direct flow of inlet air into said cooling slots.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Spray-Type Burners (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
US865273A 1968-10-18 1969-10-10 Combustion chamber for gas turbine Expired - Lifetime US3650106A (en)

Applications Claiming Priority (1)

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FR69050513 1968-10-18

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US3650106A true US3650106A (en) 1972-03-21

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US (1) US3650106A (xx)
AT (2) AT279483B (xx)
BR (1) BR6913235D0 (xx)
CA (1) CA917933A (xx)
CH (1) CH531643A (xx)
DE (3) DE1966660A1 (xx)
ES (1) ES372250A1 (xx)
FR (1) FR1592591A (xx)
GB (1) GB1251749A (xx)
NL (1) NL6915497A (xx)
SE (1) SE356332B (xx)

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5089708A (xx) * 1973-12-14 1975-07-18
JPS5242907U (xx) * 1975-09-22 1977-03-26
US4129985A (en) * 1975-11-17 1978-12-19 Kawasaki Jukogyo Kabushiki Kaisha Combustor device of gas turbine engine
US4900246A (en) * 1977-05-25 1990-02-13 Phillips Petroleum Company Apparatus for burning nitrogen-containing fuels
US5353586A (en) * 1991-04-17 1994-10-11 Rolls-Royce Plc Combustion chamber assembly with hollow support strut for carrying cooling air
EP2157286A1 (de) * 2008-08-21 2010-02-24 Siemens Aktiengesellschaft Gasturbine mit angewinkeltem Mischgehäuse und Verfahren zur Turbinenanströmung
US20110091829A1 (en) * 2009-10-20 2011-04-21 Vinayak Barve Multi-fuel combustion system
US20130081399A1 (en) * 2011-10-04 2013-04-04 David J. Wiebe Casing for a gas turbine engine
US20140130505A1 (en) * 2012-11-15 2014-05-15 General Electric Company Cross-fire tube purging arrangement and method of purging a cross-fire tube
US20140137536A1 (en) * 2012-11-21 2014-05-22 General Electric Company Super telescoping cross-fire tube and method of assembling a combustor structure
US20140144122A1 (en) * 2012-11-29 2014-05-29 General Electric Company Crossfire tube assembly between adjacent combustors
JP2015135212A (ja) * 2014-01-17 2015-07-27 ヤンマー株式会社 ガスタービンエンジン
US20160010868A1 (en) * 2014-06-13 2016-01-14 Rolls-Royce Corporation Combustor with spring-loaded crossover tubes
US20160025346A1 (en) * 2014-07-24 2016-01-28 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
EP3121381A1 (en) * 2015-07-22 2017-01-25 United Technologies Corporation Turbine engine and method of maintaining a turbine engine

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH586375A5 (xx) * 1975-06-25 1977-03-31 Bbc Brown Boveri & Cie
GB2040031B (en) * 1979-01-12 1983-02-09 Gen Electric Dual stage-dual mode low emission gas turbine combustion system
US4393651A (en) * 1980-09-02 1983-07-19 Chandler Evans Inc. Fuel control method and apparatus
US5361577A (en) * 1991-07-15 1994-11-08 General Electric Company Spring loaded cross-fire tube

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
US3172257A (en) * 1962-08-30 1965-03-09 Ingersoll Rand Co Hot gas power plant arrangement
GB998371A (en) * 1964-05-04 1965-07-14 Rolls Royce Ignition means for a continuous flow engine
US3464627A (en) * 1966-06-21 1969-09-02 Sopromi Soc Proc Modern Inject Electromagnetic fuel-injection valve

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2638745A (en) * 1943-04-01 1953-05-19 Power Jets Res & Dev Ltd Gas turbine combustor having tangential air inlets for primary and secondary air
US3172257A (en) * 1962-08-30 1965-03-09 Ingersoll Rand Co Hot gas power plant arrangement
GB998371A (en) * 1964-05-04 1965-07-14 Rolls Royce Ignition means for a continuous flow engine
US3464627A (en) * 1966-06-21 1969-09-02 Sopromi Soc Proc Modern Inject Electromagnetic fuel-injection valve

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5089708A (xx) * 1973-12-14 1975-07-18
JPS5242907U (xx) * 1975-09-22 1977-03-26
US4129985A (en) * 1975-11-17 1978-12-19 Kawasaki Jukogyo Kabushiki Kaisha Combustor device of gas turbine engine
US4900246A (en) * 1977-05-25 1990-02-13 Phillips Petroleum Company Apparatus for burning nitrogen-containing fuels
US5353586A (en) * 1991-04-17 1994-10-11 Rolls-Royce Plc Combustion chamber assembly with hollow support strut for carrying cooling air
EP2157286A1 (de) * 2008-08-21 2010-02-24 Siemens Aktiengesellschaft Gasturbine mit angewinkeltem Mischgehäuse und Verfahren zur Turbinenanströmung
US20110091829A1 (en) * 2009-10-20 2011-04-21 Vinayak Barve Multi-fuel combustion system
WO2011048123A3 (en) * 2009-10-20 2012-12-20 Siemens Aktiengesellschaft A multi-fuel combustion system
CN102844622A (zh) * 2009-10-20 2012-12-26 西门子公司 一种多燃料燃烧***
JP2013508660A (ja) * 2009-10-20 2013-03-07 シーメンス アクチエンゲゼルシヤフト 混焼システム
CN102844622B (zh) * 2009-10-20 2015-08-26 西门子公司 一种多燃料燃烧***
US20130081399A1 (en) * 2011-10-04 2013-04-04 David J. Wiebe Casing for a gas turbine engine
US9388738B2 (en) * 2011-10-04 2016-07-12 Siemens Energy, Inc. Casing for a gas turbine engine
US9328925B2 (en) * 2012-11-15 2016-05-03 General Electric Company Cross-fire tube purging arrangement and method of purging a cross-fire tube
US20140130505A1 (en) * 2012-11-15 2014-05-15 General Electric Company Cross-fire tube purging arrangement and method of purging a cross-fire tube
US20140137536A1 (en) * 2012-11-21 2014-05-22 General Electric Company Super telescoping cross-fire tube and method of assembling a combustor structure
US20140144122A1 (en) * 2012-11-29 2014-05-29 General Electric Company Crossfire tube assembly between adjacent combustors
US9353952B2 (en) * 2012-11-29 2016-05-31 General Electric Company Crossfire tube assembly with tube bias between adjacent combustors
JP2015135212A (ja) * 2014-01-17 2015-07-27 ヤンマー株式会社 ガスタービンエンジン
US20160010868A1 (en) * 2014-06-13 2016-01-14 Rolls-Royce Corporation Combustor with spring-loaded crossover tubes
US10161635B2 (en) * 2014-06-13 2018-12-25 Rolls-Royce Corporation Combustor with spring-loaded crossover tubes
US20160025346A1 (en) * 2014-07-24 2016-01-28 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
US10401031B2 (en) * 2014-07-24 2019-09-03 Mitsubishi Hitachi Power Systems, Ltd. Gas turbine combustor
EP3121381A1 (en) * 2015-07-22 2017-01-25 United Technologies Corporation Turbine engine and method of maintaining a turbine engine
US10473117B2 (en) 2015-07-22 2019-11-12 United Technologies Corporation Diffuser case for a gas powered turbine

Also Published As

Publication number Publication date
GB1251749A (xx) 1971-10-27
NL6915497A (xx) 1970-04-21
DE1966661A1 (de) 1973-07-12
BR6913235D0 (pt) 1973-01-02
AT279483B (de) 1970-03-10
SE356332B (xx) 1973-05-21
DE1946905A1 (de) 1970-05-06
DE1966660A1 (de) 1973-07-12
CA917933A (en) 1973-01-02
ES372250A1 (es) 1971-10-16
CH531643A (fr) 1972-12-15
AT301271B (de) 1972-07-15
FR1592591A (xx) 1970-05-19
DE1946905B2 (de) 1973-09-13

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