US3113431A - Combustion equipment for a gas turbine engine - Google Patents

Combustion equipment for a gas turbine engine Download PDF

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Publication number
US3113431A
US3113431A US67423A US6742360A US3113431A US 3113431 A US3113431 A US 3113431A US 67423 A US67423 A US 67423A US 6742360 A US6742360 A US 6742360A US 3113431 A US3113431 A US 3113431A
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US
United States
Prior art keywords
air
flame tube
space
internal surface
cooling air
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
Application number
US67423A
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English (en)
Inventor
Janes Ralph
Miller Stewart Crichton
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Rolls Royce PLC
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Rolls Royce PLC
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Filing date
Publication date
Application filed by Rolls Royce PLC filed Critical Rolls Royce PLC
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Publication of US3113431A publication Critical patent/US3113431A/en
Anticipated expiration legal-status Critical
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Classifications

    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F23R3/08—Arrangement of apertures along the flame tube between annular flame tube sections, e.g. flame tubes with telescopic sections
    • 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
    • F23R3/04—Air inlet arrangements
    • 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
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube

Definitions

  • This invention concerns combustion equipment for a gas turbine engine.
  • combustion equipment for a gas turbine engine comprising an air casing and a flame tube mounted therein with a. space therebetween, said flame tube comprising at least two axially consecutive portions between which is disposed a cooling air transmitting member through which air may flow from said space and over the internal surface of the flame tube so as to cool the latter, said cooling air transmitting member being formed to transmit cooling air more readily in at least one localised area in which there is a restricted flow of air from said space.
  • the cooling air transmitting member is preferably provided with apertures of varying size, the largest apertures being disposed in said localised area or areas.
  • the cooling air transmitting member may comprise a corrugated annular strip the spaces between whose corrugations constitute the said apertures, the pitch and/ or the depth of the corrugations being increased in said localised area or areas.
  • the flame tube is provided with holes through which air may flow from said space and into the flame tube so as to cool the products of combustion formed therein, said holes being arranged immediately upstream of the said cooling air transmitting member and being longitudinally aligned with the said localised area or areas thereof.
  • the obstructions may comprise flow dividing walls extending across the said holes in the flame tube.
  • the said holes are arranged in one of said flame tube portions and the dividing walls are constituted by plates carried by the flame tube portion immediately downstream of said one portion.
  • FIGURE 1 is an axial section through combustion equipment according to the present invention
  • FIGURE 2 is a section taken on the line 2-2 of FIGURE 1,
  • FIGURE 4 is an axial section through part of a modified combustion equipment according to the present invention.
  • FIG 3 is a section taken on the line 3-3 of FIGURE 5 is a section taken on the line 55 of FIGURE 4.
  • FlGURES 1-3 there is shown a combustion equipment for a gas turbine engine comprising an annular air casing having coaxial outer and inner walls ll '11. Within the air casing there are mounted a series of flame tubes i2- (only one of which is shown in the drawings), said flame tubes 12 being mounted side by side in the annular space 13 between the walls lb, 11.
  • Each of the flame tubes 12 comprises portions 14, 15, 16, 17 which are arranged successively downstream of each other.
  • the downstream ends of the flame tube portions '14, l5, l6 are of smaller diameter than, and are mounted at, or just within, the upstream ends of the frame tube portions 15, 16, 17 respectively.
  • Corrugated annular strips 18, 19, 2b, which constitute cooling air transmitting members, are interposed between the portions 14, 315, the portions l5, l6 and the portions 16, 17 respectively.
  • the wall of the flame tube portion 16 is formed with a series of circumferentially spaced holes 21 through which air may pass from the space 13 into the interior of the flame tube.
  • the upstream end of the flame tube portion 17 is formed with a radially-outwardly extending flange 22.
  • a plate 23 Extending into each of the holes 21 so as to be disposed diametrically thereof is a plate 23 which constitutes a flow dividing wall.
  • the plate 23 has a tab 24, which is welded to the flange 22.
  • the holes 21 are disposed just upstream of the strip 2d and, as is clearly shown in FIGURE 2, both the pitch and the depth of the corrugations in the strip 20 are increased in localised areas which are adjacent to and longitudinally aligned with the holes 21.
  • the upstream end of the portion 14 is provided with a fuel injector 25, the injector 25 being mounted within an annular device 26 which is adapted to impart a swirl to air passing from the inlet end 27 of the air casing and into the flame tube 12.
  • a part of the compressed air supplied to the inlet end 27 of the air casing passes through the device 26 so as to support the combustion of the fuel injected by the injector 25, the remainder of this air passing into the annular space 13.
  • a portion of the air supplied to the space 13 passes between the corrugations in the strips 18, 19, 24 as so to provide the walls or" the flame tube with a film of cooling air while another portion of the air supplied to the space l3 (known as dilution air) passes into the flame tube via the holes 2'1.
  • Dilution air flowing through the holes 21 serves to cool the products of the combustion in the flame tube to a temperature acceptable to the turbine (not shown) to which the combustion products are supplied.
  • the provision of the plates 23 across the holes 21 reduces the irregular vortex formation which otherwise tends to occur in the air passing through the holes 21 and therefore promotes air flow through these holes.
  • FIGURES 4 and 5 illustrate a modified embodiment of the invention in which the flame tube portions l6, 17 instead of having a corrugated annular strip 2t? between them, are spaced apart by an annular strip 23.
  • the strip 28 has a ring-shaped part 29, which has the same diameter as, and is located against the downstream end of the flame tube portion 16.
  • the part 29 is provided with a radially-outwardly extending web 30.
  • the Web 30, which is perforated with apertures 31, has a radially extending flange 30a and an axially directed circumferential flange 32 which has the same diameter as, and is located against the flame tube portion 17.
  • the plates 23 are secured to the flange 39a.
  • the plates 23 and holes 21 will cause a reduction in the air supply immediately downstream of these parts.
  • the apertures 31 which are adjacent to and longitudinally aligned with the plates 23 are made larger than the remaining apertures 31.
  • Combustion equipment for a gas turbine engine comprising an air casing, a flame tu e mounted in said air casing with a space therebetween, said flame tube comprising at least two axially consecutive portions, a cooling air transmitting member disposed between said flame tube portions and through which air may flow from said space and axially over the internal surface of the flame tube to cool the latter, and means associated with said flame tube and disposed upstream of the cooling air transmitting member, for directing air from said space and into said flame tube, said last-mentioned means causing the air flow in the said space downstream thereof to be restricted in a localized area, said cooling air transmitting member being constructed to transmit cooling air axially over substantially the whole circumference of the said internal surface and more readily over a region of the internal surface which is aligned with said locailzed area than over other regions of the internal surface.
  • Combustion equipment for a gas turbine engine comprising an air casing, a flame tube mounted in said air casing with a space therebetween, said flame tube comprising two axially consecutive portions, a cooling air transmitting member disposed between said flame tube portions, means providing in said cooling air transmitting member a continuous series of apertures of varying size through all of which air may flow from said space and axially over the internal surface of the flame tube to cool the latter, and means associated with said flame tube and disposed upstream of the cooling air transmitting member, for directing air from said space and into said flame tube, said last-mentioned means causing the air flow in the said space downstream thereof to be restricted in a localized area, the largest of said apertures being aligned with said localized area and being constructed to transmit cooling air more readily over a region of the internal surface which is aligned with said localized area than over all other regions of the internal surface.
  • Combustion equipment for a gas turbine engine comprising an air casing, a flame tube mounted in said air casing with a space therebetween, said flame tube comprising at least two axially consecutive portions, a corrugated annular strip disposed between said flame tube portions and between Whose corrugations air may flow from said space and arially over the internal surface of the flame tube to cool the latter, and means as sociated with said flame tube and disposed upstream of the corrugated annular strip, for directing air from said space and into said flame tube, said last-mentioned means causing the air flow in the space downstream thereof to .t be restricted in a localized area, the pitch of the corrugations in the said corrugated annular strip being greater in alignment with said localized area than elsewhere so that the corrugated annular strip transmits cooling air axially over the said internal surface more readily over a region of the internal surface which is aligned with said localized area than over other regions of the internal surface.
  • Combustion equipment for a gas turbine engine comprising an air casing, a flame tube mounted in said air casing with a space therebetween, said flame tube comprising two axially consecutive portions, a cooling air transmitting member disposed between said flame tube portions, means providing circumferentially spaced dilution air holes in the upstream flame tube portion, said dilution air holes being disposed immediately upstream of the cooling air transmitting member, said dilution air holes being formed to direct air from said space and into said flame tube and said dilution air hoels causing the air flow in the space downstream thereof to be restricted in a localized area, and means providing in said cooling air transmitting member a continuous series of apertures of varying size through all of which air may flow from said space and axially over the internal surface of the flame tube to cool the latter, the largest of said apertures being aligned with said localized area and being constructed to transmit cooling air axially over the said internal surface more readily over a region of the internal surface which is aligned with said localized area than over all
  • Combustion equipment for a gas turbine engine comprising an air casing, a flame tube mounted in said air casing with a space therebetween, said flame tube comprising two axially consecutive portions, a cooling air transmitting member disposed between said flame tube portions, means providing circumferentially spaced dilution air holes in the upstream flame tube portion, said dilution air holes being disposed immediately upstream of the cooling air transmitting member, flow dividing Walls extending across said dilution air holes, said dilution air holes being formed to direct air from said space and into said flame tube, and said dilution air holes and flow dividing walls causing the air flow in the space downstream thereof to be restricted in a localized area, and means providing in said cooling air transmitting member a continuous series of apertures of varying size through all of which air may flow from said space and axially over the internal surface of the flame tube to cool the latter, the largest of said apertures being aligned with said localized area and being constructed to transmit cooling air axially over the said internal surface more readily

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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)
US67423A 1959-11-20 1960-11-04 Combustion equipment for a gas turbine engine Expired - Lifetime US3113431A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB39549/59A GB887639A (en) 1959-11-20 1959-11-20 Combustion equipment for a gas turbine engine

Publications (1)

Publication Number Publication Date
US3113431A true US3113431A (en) 1963-12-10

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Family Applications (1)

Application Number Title Priority Date Filing Date
US67423A Expired - Lifetime US3113431A (en) 1959-11-20 1960-11-04 Combustion equipment for a gas turbine engine

Country Status (6)

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US (1) US3113431A (es)
BE (1) BE597174A (es)
DE (1) DE1155940B (es)
ES (1) ES262327A1 (es)
GB (1) GB887639A (es)
NL (2) NL127178C (es)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3359724A (en) * 1965-08-03 1967-12-26 Bristol Siddeley Engines Ltd Cooling means in combustors for gas turbine engines
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers
US5259182A (en) * 1989-12-22 1993-11-09 Hitachi, Ltd. Combustion apparatus and combustion method therein

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB943250A (en) * 1962-02-01 1963-12-04 Rolls Royce Improvements in or relating to gas turbine combustion chambers
FR2155835B1 (es) * 1971-10-08 1974-05-31 Snecma
US4132066A (en) * 1977-09-23 1979-01-02 United Technologies Corporation Combustor liner for gas turbine engine
GB2017827B (en) * 1978-04-04 1983-02-02 Gen Electric Combustor liner cooling

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2537033A (en) * 1947-07-18 1951-01-09 Westinghouse Electric Corp Gas turbine combustion chamber construction
US2658337A (en) * 1947-12-23 1953-11-10 Lucas Ltd Joseph Combustion chamber for prime movers
FR1188614A (fr) * 1956-11-21 1959-09-24 Rolls Royce Perfectionnements aux appareillages de combustion des moteurs à turbine à gaz
GB839009A (en) * 1956-11-21 1960-06-29 Rolls Royce Improvements in or relating to combustion equipment of gas turbine engines
US2973624A (en) * 1955-10-26 1961-03-07 Gen Electric Cowled dome liners

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE830267C (de) * 1947-12-23 1952-02-04 Lucas Ltd Joseph Verbrennungskammer fuer Rueckstossmotoren u. dgl. Kraftmaschinen
GB723413A (en) * 1949-07-22 1955-02-09 Lysholm Alf Improvements in combustion chambers for gas turbines, jet propulsion plants and the like
GB762596A (en) * 1954-02-18 1956-11-28 Armstrong Siddeley Motors Ltd A combustion chamber, particularly for a gas turbine engine
GB845971A (en) * 1958-07-21 1960-08-24 Gen Electric Improvements relating to combustion chambers for gas turbine engines

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2537033A (en) * 1947-07-18 1951-01-09 Westinghouse Electric Corp Gas turbine combustion chamber construction
US2658337A (en) * 1947-12-23 1953-11-10 Lucas Ltd Joseph Combustion chamber for prime movers
US2973624A (en) * 1955-10-26 1961-03-07 Gen Electric Cowled dome liners
FR1188614A (fr) * 1956-11-21 1959-09-24 Rolls Royce Perfectionnements aux appareillages de combustion des moteurs à turbine à gaz
GB839009A (en) * 1956-11-21 1960-06-29 Rolls Royce Improvements in or relating to combustion equipment of gas turbine engines
US3019605A (en) * 1956-11-21 1962-02-06 Rolls Royce Combustion apparatus of gas turbine engines with means controlling air flow conditions in the combustion apparatus

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3359724A (en) * 1965-08-03 1967-12-26 Bristol Siddeley Engines Ltd Cooling means in combustors for gas turbine engines
US3369363A (en) * 1966-01-19 1968-02-20 Gen Electric Integral spacing rings for annular combustion chambers
US5259182A (en) * 1989-12-22 1993-11-09 Hitachi, Ltd. Combustion apparatus and combustion method therein

Also Published As

Publication number Publication date
NL127178C (es)
BE597174A (fr) 1961-03-15
NL257968A (es)
DE1155940B (de) 1963-10-17
GB887639A (en) 1962-01-24
ES262327A1 (es) 1961-01-16

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