US2658339A - Sheet metal combustion chamber, flame tube, and the like - Google Patents

Sheet metal combustion chamber, flame tube, and the like Download PDF

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Publication number
US2658339A
US2658339A US255571A US25557151A US2658339A US 2658339 A US2658339 A US 2658339A US 255571 A US255571 A US 255571A US 25557151 A US25557151 A US 25557151A US 2658339 A US2658339 A US 2658339A
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United States
Prior art keywords
sheet metal
combustion chamber
flame tube
holes
metal combustion
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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
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US255571A
Inventor
Bonsall William
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ZF International UK Ltd
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Joseph Lucas Ltd
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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
    • F23R3/02—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
    • F23R3/002—Wall structures
    • 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 relates to an air-jacketed sheet metal combustion chamber, flame tube, or like body of the kind used in a jet engine, or gas turbine, or for other purposes, and in which hot gases are generated or conveyed, the surface or surfaces of the body having therein holes for the admission of air from the jacket.
  • One of the difliculties experienced when such a body is in use is the cracking of the edges of the holes due to stresses set up in the metal by the heating action of the gases, or other causes, and the object of the present invention is to enable this difiiculty to be overcome in a simple manner.
  • the invention consists in forming in the metal around the holes, transverse corrugations adapted to allow free expansion and contraction of the metal at the edges of the holes.
  • Figure 1 is a sectional side elevation of a combustion chamber or flame tube having therein air-admission holes such as are required to be formed in accordance with the invention.
  • Figures 2 and 3 are respectively a plan and cross section illustrating to a larger scale than Figure 1, a hole shaped in accordance with the invention, Figure 3 being taken on the line 33 of Figure 2.
  • the combustion chamber or flame tube a. shown in Figure 1 is of known form, and is provided with holes as b of the same or different sizes through which air can flow into the chamber or tube from a surrounding air jacket c.
  • the metal around those holes whose edges are liable to crack is subjected to the action of press tools whereby a ring of transverse corrugations d is formed around each hole.
  • These corrugations extend radially from the hole to any convenient and suitable extent, and they may be tapered in the direction of their length, the maximum depth being .at the edge of the hole.
  • the pitch and depth of the corrugations is made appropriate to the diameter of the hole and thickness of the metal, but in all cases they are such as will relieve the metal of the detrimental stresses.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Air Bags (AREA)
  • Reinforcement Elements For Buildings (AREA)

Description

Nov. 10, 1953 w. BONSALL 2,658,339
SHEET METAL COMBUSTION CHAMBER, FLAME TUBE, AND THE LIKE .Filed Nov. 9, 1951 EB 0 5L Patented Nov. 10, 1953 SHEET METAL COMBUSTION CHAIVIBER, FLAME TUBE, AND THE LIKE William Bonsall, Burnley, England, assignor to Joseph Lucas Limited, Birmingham, England Application November 9, 1951, Serial No. 255,571
Claims priority, application Great Britain November 29, 1950 1 Claim. 1
This invention relates to an air-jacketed sheet metal combustion chamber, flame tube, or like body of the kind used in a jet engine, or gas turbine, or for other purposes, and in which hot gases are generated or conveyed, the surface or surfaces of the body having therein holes for the admission of air from the jacket.
One of the difliculties experienced when such a body is in use, is the cracking of the edges of the holes due to stresses set up in the metal by the heating action of the gases, or other causes, and the object of the present invention is to enable this difiiculty to be overcome in a simple manner.
The invention consists in forming in the metal around the holes, transverse corrugations adapted to allow free expansion and contraction of the metal at the edges of the holes.
In the accompanying drawing:
Figure 1 is a sectional side elevation of a combustion chamber or flame tube having therein air-admission holes such as are required to be formed in accordance with the invention.
Figures 2 and 3 are respectively a plan and cross section illustrating to a larger scale than Figure 1, a hole shaped in accordance with the invention, Figure 3 being taken on the line 33 of Figure 2.
The combustion chamber or flame tube a. shown in Figure 1 is of known form, and is provided with holes as b of the same or different sizes through which air can flow into the chamber or tube from a surrounding air jacket c.
According to the invention, and as shown in Figures 2 and 3, the metal around those holes whose edges are liable to crack, is subjected to the action of press tools whereby a ring of transverse corrugations d is formed around each hole. These corrugations extend radially from the hole to any convenient and suitable extent, and they may be tapered in the direction of their length, the maximum depth being .at the edge of the hole. The pitch and depth of the corrugations is made appropriate to the diameter of the hole and thickness of the metal, but in all cases they are such as will relieve the metal of the detrimental stresses.
Whilst for most purposes it is convenient to treat all the holes in the manner above described, this is not essential, as the treatment may be applied only to the edges of those holes which in bodies of conventional construction have been found to be susceptible to cracking.
By this invention, cracking of the edges of the holes can be obviated in a very simple manner.
Havin this described my invention what I claim as new and desire to secure by Letters Patent is:
A sheet metal hot gas chamber of elongated form, and an air jacket surrounding said chamber, said chamber being provided with a plurality of holes through which air from said jacket is admissible to said chamber, and the sheet metal around said holes being formed with corrugations which extend radially from said holes and allow free expansion and contraction of the metal bounding said holes.
WILLIAM BONSALL.
References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 1,159,322 Livingston Nov. 2, 1915 1,581,488 Lewis Apr. 20, 1926 2,477,583 DeZubay et al Aug. 2, 1949 2,513,325 Hundstad July 4, 1950 2,543,755 Berger Mar. 6, 1951
US255571A 1950-11-29 1951-11-09 Sheet metal combustion chamber, flame tube, and the like Expired - Lifetime US2658339A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB29186/50A GB699251A (en) 1950-11-29 1950-11-29 Sheet metal combustion chambers, flame tubes and other like tubular bodies

Publications (1)

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US2658339A true US2658339A (en) 1953-11-10

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US (1) US2658339A (en)
FR (1) FR1045432A (en)
GB (1) GB699251A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2930195A (en) * 1956-02-14 1960-03-29 United Aircraft Corp Oscillating flow combustion chamber
US3220179A (en) * 1962-10-31 1965-11-30 Walter P Innes Jr Catalytic afterburner for internal combustion engines and the like
US5220795A (en) * 1991-04-16 1993-06-22 General Electric Company Method and apparatus for injecting dilution air
DE19528406A1 (en) * 1995-08-02 1997-02-06 Bmw Rolls Royce Gmbh Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension
US6101814A (en) * 1999-04-15 2000-08-15 United Technologies Corporation Low emissions can combustor with dilution hole arrangement for a turbine engine
US20060037322A1 (en) * 2003-10-09 2006-02-23 Burd Steven W Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume
US20160201908A1 (en) * 2013-08-30 2016-07-14 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
CN111365734A (en) * 2020-03-25 2020-07-03 中国船舶重工集团公司第七0三研究所 Mixed-grading ultra-low-emission flame tube

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1159322A (en) * 1914-05-20 1915-11-02 Standard Steel Wheel And Tire Armor Company Method of radially corrugating sheet metal.
US1581488A (en) * 1920-12-07 1926-04-20 Standard Steel Wheel & Tire Ar Method of and apparatus for forming radially-corrugated disks
US2477583A (en) * 1946-07-25 1949-08-02 Westinghouse Electric Corp Combustion chamber construction
US2513325A (en) * 1946-08-29 1950-07-04 Westinghouse Electric Corp Combustion apparatus
US2543755A (en) * 1946-07-25 1951-03-06 Westinghouse Electric Corp Air inlet opening arrangement for combustion chambers

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1159322A (en) * 1914-05-20 1915-11-02 Standard Steel Wheel And Tire Armor Company Method of radially corrugating sheet metal.
US1581488A (en) * 1920-12-07 1926-04-20 Standard Steel Wheel & Tire Ar Method of and apparatus for forming radially-corrugated disks
US2477583A (en) * 1946-07-25 1949-08-02 Westinghouse Electric Corp Combustion chamber construction
US2543755A (en) * 1946-07-25 1951-03-06 Westinghouse Electric Corp Air inlet opening arrangement for combustion chambers
US2513325A (en) * 1946-08-29 1950-07-04 Westinghouse Electric Corp Combustion apparatus

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2930195A (en) * 1956-02-14 1960-03-29 United Aircraft Corp Oscillating flow combustion chamber
US3220179A (en) * 1962-10-31 1965-11-30 Walter P Innes Jr Catalytic afterburner for internal combustion engines and the like
US5220795A (en) * 1991-04-16 1993-06-22 General Electric Company Method and apparatus for injecting dilution air
DE19528406A1 (en) * 1995-08-02 1997-02-06 Bmw Rolls Royce Gmbh Gas turbine combustion chamber with air transfer ports - has shot blasted, rolled raster or fluting design upstream of ports to specified raster dimension
US6101814A (en) * 1999-04-15 2000-08-15 United Technologies Corporation Low emissions can combustor with dilution hole arrangement for a turbine engine
US20060037322A1 (en) * 2003-10-09 2006-02-23 Burd Steven W Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume
US7093441B2 (en) * 2003-10-09 2006-08-22 United Technologies Corporation Gas turbine annular combustor having a first converging volume and a second converging volume, converging less gradually than the first converging volume
US20160201908A1 (en) * 2013-08-30 2016-07-14 United Technologies Corporation Vena contracta swirling dilution passages for gas turbine engine combustor
CN111365734A (en) * 2020-03-25 2020-07-03 中国船舶重工集团公司第七0三研究所 Mixed-grading ultra-low-emission flame tube

Also Published As

Publication number Publication date
GB699251A (en) 1953-11-04
FR1045432A (en) 1953-11-26

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