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US3767122A - Flame tubes - Google Patents

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Publication number
US3767122A
US3767122A US00276159A US3767122DA US3767122A US 3767122 A US3767122 A US 3767122A US 00276159 A US00276159 A US 00276159A US 3767122D A US3767122D A US 3767122DA US 3767122 A US3767122 A US 3767122A
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US
United States
Prior art keywords
tube
baffle
tube element
vanes
passage
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
US00276159A
Inventor
G Sedgwick
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Northrop Grumman Properties Ltd
Original Assignee
Lucas Aerospace Ltd
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Filing date
Publication date
Application filed by Lucas Aerospace Ltd filed Critical Lucas Aerospace Ltd
Application granted granted Critical
Publication of US3767122A publication Critical patent/US3767122A/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
    • F23R3/10—Air inlet arrangements for primary air
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes

Definitions

  • a flame tube for a gas turbine engine comprises a tubular element having an inlet and an outlet at opposite ends thereof.
  • a frusto-conical baffle is mounted at the inlet of the tube element so as to direct air enteringthe inlet against the wall of the tube element.
  • a plurality of vanes are secured to the baffle and to the tube element so as to locate the latter with respect to the baffle.
  • the vanes are mounted by means of a plate and a bush on a chamber within which the flame tube is mounted.
  • the bush receives a fuel atomizer for injectingfuelinto the tube element through an axial opening in the baffle and the air which passes into the 1,788,495 1 1931 Sh d....
  • a flametube for a gas turbine engine comprises a tube element provided at opposite ends with an inlet and an outlet, a baffle within the tube element adjacent the inlet and adapted to direct air entering the inlet against the tube element wall, said baffle having a through-passage therein, a plurality of vanes secured to the baffle and .the tube element to locate the latter with respect to the baffle, said vanes being arranged to impart a swirling motion to air directed through said through-passage and mounting means secured to said vanes, said mounting means being adapted to receive a fuel atomizing device and to engage a structure upon which the flame tube, is in use, located, said atomizing device injecting fuel into the tube element via said through-passage.
  • FIG. 1 is a section through a flame tube
  • FIG. 2 is a section on line 2-2 in FIG. 1.
  • the flame tube has a tube element provided with an inlet 11 and'an outlet 12.
  • a baffle 13 of generally frusto-conical form and having an axial through-passage l4.
  • a reinforcing ring 23 Secured to the upstream side of baffle 13 is a reinforcing ring 23.
  • vanes 15 are also secured to the tube element 10.
  • vanes 15 are tangential to an imaginary circle which is of somewhat greater diameter than the passage 14.
  • Each vane 15 has an outer portion 15b which extends radially with respect to the axis of the passage 14.
  • a further portion 150 of each vane 15 extends from the portion 15b to lie against the wall of element 10.
  • a reinforcing portion 15d extends from the portion 15c to lie against and reinforce the portion 15b of an adjacent vane 15, to reinforce the radial portions of the next adjacent vanes.
  • a mounting comprising a circular plate 16 and a bush 17 secured to the plate 16 and axially aligned with the tube element 10.
  • the bush 17 is adapted to receive a fuel atomizer shown generally at 18.
  • Bush 17 is externally threaded to receive a nut 19 by means of which the mounting is secured to an end plate 20 of a chamber within which the flame tube is mounted.
  • the plate 16 abuts the end plate 20 whereby any load on the tube element 10 is transferred via the vanes 15 to the end plate 20.
  • the tube element 10 has slots 21 through its wall intermediate the inlet 11 and outlet 12. Holes 22 also extend through the wall of element 10 downstream of slots 21.
  • fuel is supplied to the flame tube via fuel atomizer l8 and air under pressure is supplied to the chamber surrounding the flame tube.
  • Air enters the flame tube via passage 14 and is also directed against the wall of element 10 by the baffle 13.
  • the portions 15a of vanes 15 impart a swirling motion to the air passing into the tube element 10 through the axial passage 14 internally of the baffle 13.
  • Secondary combustion air and dilution air enter the flame tube via slots 21 and holes 22 respectively.
  • a flame tube for a gas turbine engine comprising a tube element provided at opposite ends with an inlet and an outlet, a baffle within the tube element adjacent the inlet and adapted to direct air entering the inlet against the tube element wall, said baffle having a through-passage therein, a plurality of vanes secured to the baffle and the tube element to locate the latter with respect to the baffle, said vanes being arranged to impart a swirling motion to air directed, through said through-passage and mounting means secured to said vanes, said mounting means receiving a fuel atomizing device and engaging a structure upon which the flame tube, is in use, located, said atomizing device injecting fuel into the tube element via said through-passage.
  • each vane has a portion which extends so as to lie against an outer portion of an adjacent vane thereby to reinforce that outer portion.
  • each vane has a portion which lies against the tube element wall.
  • the mounting means comprises a plate secured to an inner portion of each vane and a bush secured to the plate and adapted to be detachably secured to the structure and to receive the fuel atomizing device.
  • each vane has an inner end portion tangential to an imaginary circle of somewhat greater diameter than the through-passage, with said inner end portions imparting the swirling motion to the air directed through the through-passage.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
  • Pre-Mixing And Non-Premixing Gas Burner (AREA)
  • Spray-Type Burners (AREA)
  • Gas Burners (AREA)

Abstract

A flame tube for a gas turbine engine comprises a tubular element having an inlet and an outlet at opposite ends thereof. A frusto-conical baffle is mounted at the inlet of the tube element so as to direct air entering the inlet against the wall of the tube element. A plurality of vanes are secured to the baffle and to the tube element so as to locate the latter with respect to the baffle. The vanes, are mounted by means of a plate and a bush on a chamber within which the flame tube is mounted. The bush receives a fuel atomizer for injecting fuel into the tube element through an axial opening in the baffle and the air which passes into the tube element via the axial opening has a swirl imparted thereto by the vanes.

Description

United States Patent [191 Sedgwick Oct. 23, 1973 41 FLAME'TUBES [75] Inventor:' Gordon Sedgwick, Nelson, England [73] Assignee: Lucas Aerospace Limited, Birmingham, England [22] Filed: July 28, 1972 21 Appl. No.: 276,159
[30] Foreign Application Priority Data Aug. 10, 1971 Great Britain 37,447/71 [5 6] References Cited UNITED STATES PATENTS v FOREIGN PATENTS OR APPLICATIONS 869,446 3/1953 Germany 239/403 839,267 6/1960 Great Britain.... 239/405 277,101 8/1930 ltaly 239/403 Primary ExaminerRobertS. Ward, Jr. Attorney-John C. Holman et al.
[57] ABSTRACT A flame tube for a gas turbine engine comprises a tubular element having an inlet and an outlet at opposite ends thereof. A frusto-conical baffle is mounted at the inlet of the tube element so as to direct air enteringthe inlet against the wall of the tube element. A plurality of vanes are secured to the baffle and to the tube element so as to locate the latter with respect to the baffle. The vanes, are mounted by means of a plate and a bush on a chamber within which the flame tube is mounted. The bush receives a fuel atomizer for injectingfuelinto the tube element through an axial opening in the baffle and the air which passes into the 1,788,495 1 1931 Sh d.... 39 3 I 1991894 2 5 532;: 2 3: tube element via the axial opening has a SWll'l 1m- 2,210,428 8/1940 I P655311] 235/39 x parted thereto by the vanes- 2,366,605 1/ 1945 Evans 239/430 X 6 Claims, 2 Drawing Figures 2,414,442 1/1947 Breault 239/430 X 3,700,173 10/1972 Ketchum ..239/405 X l l I I 1 I I II II 1 FLAME TUBES BACKGROUND OF THE INVENTION This invention relates to flame tubes for gas turbine engines, and has an an object to provide a flame tube in a convenient form.
SUMMARY OF THE INVENTION According to the invention, a flametube for a gas turbine engine comprises a tube element provided at opposite ends with an inlet and an outlet, a baffle within the tube element adjacent the inlet and adapted to direct air entering the inlet against the tube element wall, said baffle having a through-passage therein, a plurality of vanes secured to the baffle and .the tube element to locate the latter with respect to the baffle, said vanes being arranged to impart a swirling motion to air directed through said through-passage and mounting means secured to said vanes, said mounting means being adapted to receive a fuel atomizing device and to engage a structure upon which the flame tube, is in use, located, said atomizing device injecting fuel into the tube element via said through-passage.
An example of a flame tube according to the invention will now be described with reference to the accompanying drawings in which:
BRIEF DESCRIPTION OF THE DRAWINGS 1 FIG. 1 is a section through a flame tube, and FIG. 2 is a section on line 2-2 in FIG. 1.
DETAILED DESCRIPTION OF THE INVENTION The flame tube has a tube element provided with an inlet 11 and'an outlet 12. Within the inlet end of element 10 is a baffle 13 of generally frusto-conical form and having an axial through-passage l4. Secured to the upstream side of baffle 13 is a reinforcing ring 23. Secured to ring 23 are a plurality of vanes 15, which are also secured to the tube element 10. As seen in FIG. 2 at their inner ends 15b vanes 15 are tangential to an imaginary circle which is of somewhat greater diameter than the passage 14. Each vane 15 has an outer portion 15b which extends radially with respect to the axis of the passage 14. A further portion 150 of each vane 15 extends from the portion 15b to lie against the wall of element 10. A reinforcing portion 15d extends from the portion 15c to lie against and reinforce the portion 15b of an adjacent vane 15, to reinforce the radial portions of the next adjacent vanes. Secured to the portions 150 of the vanes is a mounting comprising a circular plate 16 and a bush 17 secured to the plate 16 and axially aligned with the tube element 10.
The bush 17 is adapted to receive a fuel atomizer shown generally at 18. Bush 17 is externally threaded to receive a nut 19 by means of which the mounting is secured to an end plate 20 of a chamber within which the flame tube is mounted. The plate 16 abuts the end plate 20 whereby any load on the tube element 10 is transferred via the vanes 15 to the end plate 20.
The tube element 10 has slots 21 through its wall intermediate the inlet 11 and outlet 12. Holes 22 also extend through the wall of element 10 downstream of slots 21.
In use, fuel is supplied to the flame tube via fuel atomizer l8 and air under pressure is supplied to the chamber surrounding the flame tube. Air enters the flame tube via passage 14 and is also directed against the wall of element 10 by the baffle 13. The portions 15a of vanes 15 impart a swirling motion to the air passing into the tube element 10 through the axial passage 14 internally of the baffle 13. Secondary combustion air and dilution air enter the flame tube via slots 21 and holes 22 respectively. I
I claim:
1. A flame tube for a gas turbine engine, comprising a tube element provided at opposite ends with an inlet and an outlet, a baffle within the tube element adjacent the inlet and adapted to direct air entering the inlet against the tube element wall, said baffle having a through-passage therein, a plurality of vanes secured to the baffle and the tube element to locate the latter with respect to the baffle, said vanes being arranged to impart a swirling motion to air directed, through said through-passage and mounting means secured to said vanes, said mounting means receiving a fuel atomizing device and engaging a structure upon which the flame tube, is in use, located, said atomizing device injecting fuel into the tube element via said through-passage.
2. The flame tube as claimed in claim I, wherein each vane has a portion which extends so as to lie against an outer portion of an adjacent vane thereby to reinforce that outer portion.
3. The flame tube as claimed in claim 1, wherein each vane has a portion which lies against the tube element wall.
4. The flame tube as claimed in claim 1, wherein the mounting means comprises a plate secured to an inner portion of each vane and a bush secured to the plate and adapted to be detachably secured to the structure and to receive the fuel atomizing device.
5. The flame tube as claimed inclaim 4, wherein the bush is externally screw-threaded to engage a nut rigidly connected with said structure.
6. The flame tube as claimed in claim 1, wherein each vane has an inner end portion tangential to an imaginary circle of somewhat greater diameter than the through-passage, with said inner end portions imparting the swirling motion to the air directed through the through-passage.

Claims (6)

1. A flame tube for a gas turbine engine, comprising a tube element provided at opposite ends with an inlet and an outlet, a baffle within the tube element adjacent the inlet and adapted to direct air entering the inlet against the tube element wall, said baffle having a through-passage therein, a plurality of vanes secured to the baffle and the tube element to locate the latter with respect to the baffle, said vanes being arranged to impart a swirling motion to air directed, through said through-passage and mounting means secured to said vanes, said mounting means receiving a fuel atomizing device and engaging a structure upon which the flame tube, is in use, located, said atomizing device injecting fuel into the tube element via said through-passage.
2. The flame tube as claimed in claim 1, wherein each vane has a portion which extends so as to lie against an outer portion of an adjacent vane thereby to reinforce that outer portion.
3. The flame tube as claimed in claim 1, wherein each vane has a portion which lies against the tube element wall.
4. The flame tube as claimed in claim 1, wherein the mounting means comprises a plate secured to an inner portion of each vane and a bush secured to the plate and adapted to be detachably secured to the structure and to receive the fuel atomizing device.
5. The flame tube as claimed in claim 4, wherein the bush is externally screw-threaded to engage a nut rigidly connected with said structure.
6. The flame tube as claimed in claim 1, wherein each vane has an inner end portion tangential to an imaginary circle of somewhat greater diameter than the through-passage, with said inner end portions imparting the swirling motion to the air directed through the through-passage.
US00276159A 1971-08-10 1972-07-28 Flame tubes Expired - Lifetime US3767122A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3744771A GB1394223A (en) 1971-08-10 1971-08-10 Flame tubes

Publications (1)

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US3767122A true US3767122A (en) 1973-10-23

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US00276159A Expired - Lifetime US3767122A (en) 1971-08-10 1972-07-28 Flame tubes

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US (1) US3767122A (en)
JP (1) JPS5246325B2 (en)
DE (1) DE2239079C3 (en)
FR (1) FR2148474B1 (en)
GB (1) GB1394223A (en)
IT (1) IT961918B (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103486618A (en) * 2013-09-29 2014-01-01 北京动力机械研究所 Cyclone for aviation gas turbine engine
CN103528095A (en) * 2012-07-06 2014-01-22 株式会社日立制作所 Gas turbine combustor and operating method for gas turbine combustor
US20160223196A1 (en) * 2015-02-02 2016-08-04 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Crude Oil Spray Combustor
US9416682B2 (en) 2012-12-11 2016-08-16 United Technologies Corporation Turbine engine alignment assembly
US11371701B1 (en) * 2021-02-03 2022-06-28 General Electric Company Combustor for a gas turbine engine
US20230137910A1 (en) * 2021-11-03 2023-05-04 General Electric Company Wavy annular dilution slots for lower emissions

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS50149003A (en) * 1974-05-22 1975-11-28
JPS56155510A (en) * 1980-04-30 1981-12-01 Tohoku Metal Ind Ltd Metal dust magnetic core
CN108443911B (en) * 2018-01-23 2020-06-19 中科合肥微小型燃气轮机研究院有限责任公司 An orifice type air atomizing nozzle
CN114087625A (en) * 2021-12-01 2022-02-25 北京动力机械研究所 Self-adaptive swirler device with adjustable blade angle

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1788495A (en) * 1928-09-01 1931-01-13 Sheppard Walter Harry Oil burner
US1991894A (en) * 1931-08-26 1935-02-19 Ross H Forney Combination gas and oil burner
US2210428A (en) * 1939-01-19 1940-08-06 Peabody Engineering Corp Air register control
US2366605A (en) * 1943-04-01 1945-01-02 Evans John Louis Blowtorch
US2414442A (en) * 1944-02-03 1947-01-21 Delphis C Breault Burner construction
DE869446C (en) * 1950-09-04 1953-03-05 Brown Ag Metal combustion chamber for the generation of hot gases, especially propellants for gas turbine systems
GB839267A (en) * 1957-11-28 1960-06-29 Lucas Industries Ltd Liquid fuel combustion apparatus
US3700173A (en) * 1970-12-30 1972-10-24 Combustion Eng Diffuser

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1788495A (en) * 1928-09-01 1931-01-13 Sheppard Walter Harry Oil burner
US1991894A (en) * 1931-08-26 1935-02-19 Ross H Forney Combination gas and oil burner
US2210428A (en) * 1939-01-19 1940-08-06 Peabody Engineering Corp Air register control
US2366605A (en) * 1943-04-01 1945-01-02 Evans John Louis Blowtorch
US2414442A (en) * 1944-02-03 1947-01-21 Delphis C Breault Burner construction
DE869446C (en) * 1950-09-04 1953-03-05 Brown Ag Metal combustion chamber for the generation of hot gases, especially propellants for gas turbine systems
GB839267A (en) * 1957-11-28 1960-06-29 Lucas Industries Ltd Liquid fuel combustion apparatus
US3700173A (en) * 1970-12-30 1972-10-24 Combustion Eng Diffuser

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103528095A (en) * 2012-07-06 2014-01-22 株式会社日立制作所 Gas turbine combustor and operating method for gas turbine combustor
CN103528095B (en) * 2012-07-06 2015-08-26 三菱日立电力系统株式会社 The application method of gas turbine burner and gas turbine burner
US9416682B2 (en) 2012-12-11 2016-08-16 United Technologies Corporation Turbine engine alignment assembly
CN103486618A (en) * 2013-09-29 2014-01-01 北京动力机械研究所 Cyclone for aviation gas turbine engine
CN103486618B (en) * 2013-09-29 2015-07-01 北京动力机械研究所 Cyclone for aviation gas turbine engine
US20160223196A1 (en) * 2015-02-02 2016-08-04 The Government Of The United States Of America, As Represented By The Secretary Of The Navy Crude Oil Spray Combustor
US11371701B1 (en) * 2021-02-03 2022-06-28 General Electric Company Combustor for a gas turbine engine
CN114857618A (en) * 2021-02-03 2022-08-05 通用电气公司 burners for gas turbine engines
US11549686B2 (en) 2021-02-03 2023-01-10 General Electric Company Combustor for a gas turbine engine
US20230137910A1 (en) * 2021-11-03 2023-05-04 General Electric Company Wavy annular dilution slots for lower emissions
US11920790B2 (en) * 2021-11-03 2024-03-05 General Electric Company Wavy annular dilution slots for lower emissions

Also Published As

Publication number Publication date
IT961918B (en) 1973-12-10
JPS4827115A (en) 1973-04-10
DE2239079B2 (en) 1979-08-09
JPS5246325B2 (en) 1977-11-24
DE2239079C3 (en) 1980-04-17
GB1394223A (en) 1975-05-14
FR2148474A1 (en) 1973-03-23
DE2239079A1 (en) 1973-02-15
FR2148474B1 (en) 1976-05-14

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