Search Images Maps Play YouTube News Gmail Drive More »
Sign in
Screen reader users: click this link for accessible mode. Accessible mode has the same essential features but works better with your reader.


  1. Advanced Patent Search
Publication numberUS2654219 A
Publication typeGrant
Publication dateOct 6, 1953
Filing dateAug 28, 1951
Priority dateSep 4, 1950
Also published asDE869446C
Publication numberUS 2654219 A, US 2654219A, US-A-2654219, US2654219 A, US2654219A
InventorsTadeusz Zaba
Original AssigneeBbc Brown Boveri & Cie
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Metal combustion chamber
US 2654219 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

Oct. 6, 1953 T. ZABA METAL COMBUSTION CHAMBER Filed Aug. 28, 1951 7 v 2 a 0 0 I o 0 Q o c m Q Q 0 0 0 0 0 0 0 2v e o o o o 0 0 0 O 0 0 s o o 0 0 v o, Ma omomomo omol w e o 0 0 0 0 0 0 0 o o 0 o o o o o 4 090 0 0 0 0 0 0 0 0 0 0 0 0 UT] M m 4 6 7 3 b J ATTORNEYS.

Patented Oct. 6, 1953 METAL COMBUSTION CHAMBER Tadeusz Zaba, Wettingen, Switzerland, assignor to Aktiengesellschaft Brown, Boveri & Cie., Baden, Switzerland, a joint-stock company Application August 28, 1951, Serial No. 244,047 In Switzerland September 4, 1950 6 Claims.

This invention relates to metal combustion chambers for the generation of hot pressure gases for various industrial purposes, and more particularly to combustion chambers for producing fuel gases for gas turbine plants,

It is known to produce hot combustion gases, and particularly hot pressure gases for gas turbine plants, in metal combustion chambers of generally cylindrical form having an outer wall or shell into which air introduced under pressure and an inner wall or shell within which the combustion takes place. The inner wall which delined the combustion space was cooled by the annular stream of air flowing through the interspace between the walls and alsoby air flowing radially into the combustion space through openings in the inner wall to form a boundary layer of cooling air flowing along the inner surface of the inner wall. The air for combustion and cooling was of course introduced under a igher pressure than that developed in the combustion space and, in the prior combustion chamhers, the inner wall where directly heated by the flame was strongly stressed by the full pressure drop between the outer air space and the combustion space. Furthermore, with some of the prior constructions, the cooling air was introduced into the combustion space at such high speed and volume as to effect a too vigorous cooling of the flame.

Objects of the present invention are to provide metal combustion chambers which eliminate such defects or disadvantages of the prior equipment and which substantially reduce the mechanical stresses imposed upon the metal wall which is directly exposed to the combustion flame. Objects are to provide metal combustion chambers of the double-walled type in which the inner wall is formed by a plurality of concentric perforated shells connected at their opposite ends only a fraction of the pressure drop between the outer shell and the combustion space. More specifically, objects of the invention are to pro vide metal combustion chambers of the character above-stated in which the total area of the perforations of the innermost shell of the inner wall is at least equal to the total area of the perforations of the outer shell or shells.

These and other objects and the advantages of the invention will be apparent from the following specification when taken. with the accompanying drawing in which:

Fig. 1 is a central vertical section through a metal combustion chamber embodying the invention; and

Fig. 2 is a fragmentary vertical section through another inner wall construction embodying the invention.

In Fig. 1, the reference numeral l identifies the conduit through which pressure air is introduced into the outer cylindrical pressure-resistant casing or shell 2 of the combustion chamber. The combustion space extends axially of and is radially spaced from the casing 2 by an inner wall 3 comprising concentric perforated shells 3a, 3b which surround the flame zone, and a cylindrical sleeve 4 which is telescoped over and radially spaced from the multiple shell wall 3. The annular space between the shells 3a, 3b is closed at its lower end by an imperforate anulus 3c, and is closed at its upper end by the conical wall 5 forming the outer boundary of the primary air inlet to the combustion zone. The fuel nozzle 8 extends axially through the hollowv conical chamber 1 which forms the inner boundary of the annular inlet for the primary combustion air and whose end walls are perforated for the flow of cooling air around the tip of the fuel nozzle. Inclined or curved vanes 8 of known type extend across the air inlet opening to impart a tangential component or swirl to the annular air stream which is introduced around the fuel stream projected from the nozzle 6.

The shells 3a and 3b of the inner wall portion are perforated for the radial flow of air for combustion and cooling, and preferably are provided with a multiplicity of relatively small perforations 9 and i0 respectively. The perforations are distributed over the entire extent of each shell, and preferably are uniformly distibuted and so dimensioned and closely arranged that a circumferentially complete layer of cooling and secondary combustion air is formed at and flows along the inner surface of the innermost shell 3b. The total area of the perforations I ll of the inner shell 3b is preferably equal to or greater than the total area of the perforations 9 of the outer shell 3a, whereby the inner shell-is stressed by about one-half or less of the total pressure drop of the combustion and cooling air flowing through the inner wall.

Additional cooling air may be introduced around or combined with the combustion gases through the annular interspaces H and I2 between the sleeve 4 and, respectively, the wall portion 3 and the casing 2, and through radial openings l3 through the sleeve 6.

The inner wall membersmay be supported on and axially of the outer casing 2 in any desired manner. When, as illustrated, the combustion chamber is vertically arranged, the wall 3 and sleeve 4 may be provided with radially spaced lugs M and 15, respectively, for supporting the same upon lugs 16 and all respectively welded or otherwise secured to the inner surface of the casing 2.

As shown somewhat schematically in Fig. 2, the inner wall 30 of the combustion'chamber may include more than two perforated sleeves, and specifically three sleeves 3114 9100 with perforations 3la-3lc respectively. The'total area of the perforations 31b of the sleeve 3% surrounding the innermost sleeve 300 is preferablyless than the total area of the perforations .of the. nther sleeves of the inner wall 30.

The advantages of the invention are that the inner shell which is most endangered by the high combustion temperatures isrelievedfrom azheavy mechanical stress and-may therefore :be .of lighter weight than in prior constructions. The .azlr enters the --combustion--zone:at-relatively low speed through the multiplicity of perforations and thereby avoids an intensive cooling of the flame, and the multiplicityof :small air jets which impinge upon the outer surface of the innermost jacket afiord a very efficient cooling .of that jacket.

It is to be understood that the invention 'is not limited to the particular constructions herein illustrated and described as 'variousmodifications which may occur .to "those familiar with the art fall within the spirit and scope of the invention as set forth in the following claims.

I claim:

1. A .metallcombustionchamher for the production of hot gases; said lchamher comprising :an outer wall providing .a pressure-resistant tea-sing having an inlet for air :under pressure, an inner 'wall within and spaced from said casing wall by an interspace through which the pressure air may flow, said inner wall comprising a plu alit .of concentrically arranged perforated shells and imperforate annular walls connecting the adjashells of .said inner wall are distributed substantially 'nrfiform'ly over the entire extent thereof.

3. A metal combustion chamber as recited in claim :1, wherein the perforations of the innermostshellof :said inner wall are closely arranged to constitute means forming a layer of cooling and combustion air flowing along the inner surface of said innermost .wall and surrounding the combustion gases.

4. Azmetal .com'bustion chamber as recited claim 1, wherein'thetotal area of the perforations of the innermost shell of said .inner wall is not less than the total area of the perforations of an outwardly arranged shell of said inner wall.

5. A :metal combustion chamber as recited in claim '1, wherein the total area of the perforations of said innermost shell is greater than that of an outer shell.

6. A metal combustion chamber as recited in claim 1, wherein saidinner wall comprises three other shells.


References Cited in the file of this patent UNITED STATES PATENTS Number Name Date 812,513 Moreno et a1. Feb. 13, 1906 2464;954 Stephens July 4, 1-939 2398528 :Way 'Feb. 28, 1950

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US812513 *Feb 27, 1905Feb 13, 1906Luigi MorenoApparatus for burning gas.
US2164954 *Oct 6, 1936Jul 4, 1939Stephens Thomas JCombustion and gas mixing assembly for gas circulating systems
US2498728 *May 7, 1948Feb 28, 1950Westinghouse Electric CorpCombustion apparatus
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2775293 *Sep 16, 1952Dec 25, 1956Hupp CorpLiquid fuel fired heating apparatus for use, especially on automotive conveyances
US2777291 *May 10, 1952Jan 15, 1957Parsons & Marine Eng TurbineCombustion chamber with removable flame tubes
US2919549 *Jan 27, 1955Jan 5, 1960Rolls RoyceHeat-resisting wall structures
US3016703 *Jan 27, 1958Jan 16, 1962English Electric Co LtdCombustion chambers
US3057611 *Feb 15, 1960Oct 9, 1962Bjerkan Engineering Service InBurner-blower combination for grain dryers
US3185458 *May 13, 1963May 25, 1965Zink Co JohnDirect fired air heater
US3220460 *Apr 12, 1963Nov 30, 1965Colt Ventilation & Heating LtdHeat generators
US3251356 *Feb 20, 1963May 17, 1966Hupp CorpRadiant heating device
US3443799 *Dec 19, 1966May 13, 1969Alco Standard CorpAir heating systems
US3463467 *May 29, 1967Aug 26, 1969Midland Ross CorpAll-metal high capacity burner
US3576384 *Nov 29, 1968Apr 27, 1971British American Oil CoMultinozzle system for vortex burners
US3729287 *Aug 23, 1971Apr 24, 1973Amoco Prod CoFlare windshield
US3861590 *May 2, 1973Jan 21, 1975Eberspaecher JSpace heater particularly for vehicles
US3922851 *Apr 5, 1974Dec 2, 1975Gen Motors CorpCombustor liner support
US3975141 *Jun 25, 1974Aug 17, 1976The United States Of America As Represented By The Secretary Of The ArmyCombustion liner swirler
US3998581 *May 12, 1975Dec 21, 1976Hotwork International LimitedGaseous fuel burners
US4141213 *Jun 23, 1977Feb 27, 1979General Motors CorporationPilot flame tube
US4174608 *Feb 7, 1977Nov 20, 1979Stal-Laval Turbin AbCombustion chamber for a gas turbine
US4276018 *May 30, 1979Jun 30, 1981Davey Compressor Co.Mobile heater
US4315406 *Apr 7, 1980Feb 16, 1982Rolls-Royce LimitedPerforate laminated material and combustion chambers made therefrom
US4626201 *Jun 11, 1985Dec 2, 1986Grantham Charles RCombustion chamber for a commercial laundry dryer
US4763481 *Jun 4, 1986Aug 16, 1988Ruston Gas Turbines LimitedCombustor for gas turbine engine
US5096412 *Jan 28, 1991Mar 17, 1992The United States Of America As Represented By The Secretary Of The ArmyCombustion chamber for multi-fuel fired ovens and griddles
US6349467 *Sep 1, 1999Feb 26, 2002General Electric CompanyProcess for manufacturing deflector plate for gas turbin engine combustors
US6351947Apr 4, 2000Mar 5, 2002Abb Alstom Power (Schweiz)Combustion chamber for a gas turbine
US6394795Aug 9, 2001May 28, 2002Eclipse, Inc.Air heating burner
US6837051 *Sep 29, 2003Jan 4, 2005Mitsubishi Heavy Industries, Ltd.Gas turbine combustor
US6964170Apr 28, 2003Nov 15, 2005Pratt & Whitney Canada Corp.Noise reducing combustor
US6971242 *Mar 2, 2004Dec 6, 2005Caterpillar Inc.Burner for a gas turbine engine
US7628020May 26, 2006Dec 8, 2009Pratt & Whitney Canada CororationCombustor with improved swirl
US7762074 *Apr 4, 2006Jul 27, 2010Siemens Energy, Inc.Air flow conditioner for a combustor can of a gas turbine engine
US7788926Aug 18, 2006Sep 7, 2010Siemens Energy, Inc.Resonator device at junction of combustor and combustion chamber
US7856830May 26, 2006Dec 28, 2010Pratt & Whitney Canada Corp.Noise reducing combustor
US8104288 *Sep 25, 2008Jan 31, 2012Honeywell International Inc.Effusion cooling techniques for combustors in engine assemblies
US8622737 *Jul 16, 2008Jan 7, 2014Robert S. BabingtonPerforated flame tube for a liquid fuel burner
US20100015562 *Jul 16, 2008Jan 21, 2010Babington Robert SPerforated flame tube for a liquid fuel burner
EP0204553A1 *Jun 4, 1986Dec 10, 1986Ruston Gas Turbines LimitedCombustor for gas turbine engine
EP0990851A1 *Sep 30, 1998Apr 5, 2000Asea Brown Boveri AGGas turbine combustor
U.S. Classification60/752, 431/351, 432/222
International ClassificationF23R3/00
Cooperative ClassificationF05B2260/201, F23R3/002
European ClassificationF23R3/00B