US3082603A - Combustion chamber with primary and secondary air flows - Google Patents

Combustion chamber with primary and secondary air flows Download PDF

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Publication number
US3082603A
US3082603A US613497A US61349756A US3082603A US 3082603 A US3082603 A US 3082603A US 613497 A US613497 A US 613497A US 61349756 A US61349756 A US 61349756A US 3082603 A US3082603 A US 3082603A
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United States
Prior art keywords
tube
combustion chamber
flame
primary
secondary air
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Expired - Lifetime
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US613497A
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English (en)
Inventor
Hering Hans
Menz Lothar
Caffier Edouard
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Safran Aircraft Engines SAS
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SNECMA SAS
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Publication date
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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

Definitions

  • the present invention has for its object a combustion chamber device which complies to a very great extent with the requirements of efiiciency, low limit of extinction, small pressure losses and good distribution of temperatures.
  • the combustion chamber proper or flametube comprises a reduced section in an intermediate portion on the downstream side of the points of admission of primary air and of fuel.
  • the reduction in section of the combustion chamber may be obtained by means of projections formed over all or part of the periphery of the said chamber.
  • Orifices for the supply of secondary air are provided in the combustion chamber on the downstream side of the reduced portion and on the upstream side of the admission to the turbine.
  • a suitable arrangement of these orifices enables the secondary air to be mixed with the gases produced by the primary combustion so as to obtain a mixing eflect which further contributes to the uniformity of temperatures.
  • FIGURE 1 is a diagrammatic longitudinal section of an arrangement embodying the invention
  • FIGURE 2 is a similar view of a modified form:
  • FIG. 1 shows a combustion chamber which may in the first place be assumed to be tubular for the sake of clearness of explanation, that is to say it comprises a mean axis A-A located inside this chamber.
  • the air supplied from the compressor arrives through the conduit 1 ice and divides into two parts, one part forming the primary air of combustion passing in the direction of the arrows f into the combustion chamber proper or flame-tube 2, through one or a number of orifices formed in the head of this tube, the other part of the air circulating inside the space formed between the flame-tube 2 and the flared conduit 1a and passing into the said flame-tube towards its end portion.
  • the example given in the drawing shows an admission device for primary air of known type, comprising two concentric open tubes 3, 4 of frusto-conical shape, connected to each other by radial arms 5.
  • the fuel injector 6 discharges in the axis of the internal tube 3.
  • a part of the primary air which passes in through the large orifice 7 formed at the head of the tube 2 passes through the annular space between the internal tube 3' and the injector 6.
  • the greater part of the primary air passes into the channels formed all around the tube 3 by this tube itself, the radial arms -5 and the peripheraleral tube 4.
  • the radial arms form wake zones on the downstream side of the flow, in which the flame may be initiated and stabilized.
  • burner devices which also comprise stabilizing screens playing the same part as the radial arms 5, in order to create wake zones in which the flame may be stabilized. Whatever may be the nature of the device, measurements made in the same rectangular cross-section of the tube 2 show the existence of zones in which the temperature is excessive and which coincide with the wake of the screens.
  • the form of embodiment of the invention shown in FIG. 1 comprises a narrowed portion 8 of the tube 2 at a certain distance on the downstream side of the origin of this tube, followed by a sharp flared portion 9 of the wall of the tube.
  • the narrowed section 8 imposes a contraction on the jet of gas in course of ignition.
  • the streams of burnt gases at high temperature and the less hot streams of air are thus displaced transversely by the efiect of the contraction, brought into intimate contact and mixed together, which eliminates the local peaks of temperature.
  • the abrupt flaring 9 of the wall following the narrowed portion 8 produces an expansion of the jet with a reduction in its speed, but as the divergence is greater than that of the divergent portion of a correct diffuser, the jet leaves the wall 9 and produces vortices, which is also favorable to uniformity of temperature.
  • the passage of the jet through the narrowed portion 8 produces a loss of pressure which facilitates the intake of secondary air through the orifices such as 10 formed on the downstream side of the said narrowed portion.
  • the gases which are admitted to the distributor d of the turbine have a better distribution of temperature than is the case with present devices.
  • the distance which separates the reduced portion 8 from the head portion of the flame-tube, and also the amount of this reduction (ratio of cross-sections) may be determine d by experiment in each particular case.
  • FIG. 1 shows a narrowed portion, the distance of which from the origin of the tube 2 is a little greater than half the length of this tube between its intake and its outlet towards the distributor d of the turbine, while the diameter of the narrowed sections is ap proximately half the diameter of the tube on the upstream side of the narrowed portion.
  • FIG. 2 differs from that described above by the presence of two successive narrowed portions 8 and 8a, which play their part in succession in creating uniform temperature condition.
  • a combustion chamber comprising a flame-tube ex tending therein in a fore-and-aft direction and bounding an inner space separated from a surrounding outer space of said chamber, saidjflame-tube having, in an intermedi ate zone thereof, a sudden constriction smoothly connected with a divergent downstream section, the portion of said inner space upstream of said constriction being gastightly separated from the surrounding outer space 4. whereas the portion of said inner space downstream of said constriction communicates with said outer space through ports formed in the divergent section of the flame-tube.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Testing Of Engines (AREA)
  • Measuring Fluid Pressure (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US613497A 1955-10-28 1956-10-02 Combustion chamber with primary and secondary air flows Expired - Lifetime US3082603A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1135017T 1955-10-28

Publications (1)

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US3082603A true US3082603A (en) 1963-03-26

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US613497A Expired - Lifetime US3082603A (en) 1955-10-28 1956-10-02 Combustion chamber with primary and secondary air flows

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US (1) US3082603A (enrdf_load_html_response)
BE (1) BE551418A (enrdf_load_html_response)
FR (1) FR1135017A (enrdf_load_html_response)
GB (1) GB812201A (enrdf_load_html_response)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3808802A (en) * 1971-04-01 1974-05-07 Toyoda Chuo Kenkyusho Kk Vortex combustor
US4265615A (en) * 1978-12-11 1981-05-05 United Technologies Corporation Fuel injection system for low emission burners
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
US5884484A (en) * 1995-06-21 1999-03-23 Mitsubishi Heavy Industries, Ltd. Combustor having a duct with a reduced portion and an orifice plate
US6021570A (en) * 1997-11-20 2000-02-08 Caterpillar Inc. Annular one piece combustor liner
US20040003599A1 (en) * 2002-07-03 2004-01-08 Ingram Joe Britt Microturbine with auxiliary air tubes for NOx emission reduction
GB2441342A (en) * 2006-09-01 2008-03-05 Rolls Royce Plc Wall Elements for Gas Turbine Engine Components
US20110203286A1 (en) * 2010-02-22 2011-08-25 United Technologies Corporation 3d non-axisymmetric combustor liner
US20120047901A1 (en) * 2010-08-16 2012-03-01 Alstom Technology Ltd. Reheat burner
US11747019B1 (en) * 2022-09-02 2023-09-05 General Electric Company Aerodynamic combustor liner design for emissions reductions

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2406075A1 (fr) * 1977-10-11 1979-05-11 Snecma Appareil de combustion et son procede de realisation
DE19649486A1 (de) * 1996-11-29 1998-06-04 Abb Research Ltd Brennkammer
JP2011102669A (ja) 2009-11-10 2011-05-26 Mitsubishi Heavy Ind Ltd ガスタービン燃焼器及びガスタービン

Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US945967A (en) * 1909-07-14 1910-01-11 Julius A Mahr Oil-burner.
FR962581A (enrdf_load_html_response) * 1950-06-16
US2525206A (en) * 1944-12-13 1950-10-10 Lucas Ltd Joseph Multiple truncated conical element combustion chamber
US2546432A (en) * 1944-03-20 1951-03-27 Power Jets Res & Dev Ltd Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
FR998079A (fr) * 1958-08-22 1952-01-14 Snecma Dispositif pour l'entrée de l'air dans la zone primaire d'une chambre de combustion de turbo-machine
GB687667A (en) * 1950-04-03 1953-02-18 Bristol Aeroplane Co Ltd Improvements in or relating to combustion systems
US2644512A (en) * 1949-06-13 1953-07-07 Heizmotoren Ges Uberlingen Am Burner device having heat exchange and gas flow control means for maintaining pyrophoric ignition therein
US2687010A (en) * 1947-11-03 1954-08-24 Power Jets Res & Dev Ltd Combustion apparatus
US2699648A (en) * 1950-10-03 1955-01-18 Gen Electric Combustor sectional liner structure with annular inlet nozzles
GB726491A (en) * 1952-07-16 1955-03-16 Onera (Off Nat Aerospatiale) Improvements in internal combustion engines through which a continuous gaseous stream is flowing and in particular in turbo-jet and turbo-prop engines
US2825202A (en) * 1950-06-19 1958-03-04 Snecma Pipes traversed by pulsating flow gases
US2828609A (en) * 1950-04-03 1958-04-01 Bristol Aero Engines Ltd Combustion chambers including suddenly enlarged chamber portions
US2907171A (en) * 1954-02-15 1959-10-06 Lysholm Alf Combustion chamber inlet for thermal power plants

Patent Citations (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR962581A (enrdf_load_html_response) * 1950-06-16
US945967A (en) * 1909-07-14 1910-01-11 Julius A Mahr Oil-burner.
US2546432A (en) * 1944-03-20 1951-03-27 Power Jets Res & Dev Ltd Apparatus for deflecting a fuel jet towards a region of turbulence in a propulsive gaseous stream
US2525206A (en) * 1944-12-13 1950-10-10 Lucas Ltd Joseph Multiple truncated conical element combustion chamber
US2687010A (en) * 1947-11-03 1954-08-24 Power Jets Res & Dev Ltd Combustion apparatus
US2644512A (en) * 1949-06-13 1953-07-07 Heizmotoren Ges Uberlingen Am Burner device having heat exchange and gas flow control means for maintaining pyrophoric ignition therein
GB687667A (en) * 1950-04-03 1953-02-18 Bristol Aeroplane Co Ltd Improvements in or relating to combustion systems
US2828609A (en) * 1950-04-03 1958-04-01 Bristol Aero Engines Ltd Combustion chambers including suddenly enlarged chamber portions
US2825202A (en) * 1950-06-19 1958-03-04 Snecma Pipes traversed by pulsating flow gases
US2699648A (en) * 1950-10-03 1955-01-18 Gen Electric Combustor sectional liner structure with annular inlet nozzles
GB726491A (en) * 1952-07-16 1955-03-16 Onera (Off Nat Aerospatiale) Improvements in internal combustion engines through which a continuous gaseous stream is flowing and in particular in turbo-jet and turbo-prop engines
US2907171A (en) * 1954-02-15 1959-10-06 Lysholm Alf Combustion chamber inlet for thermal power plants
FR998079A (fr) * 1958-08-22 1952-01-14 Snecma Dispositif pour l'entrée de l'air dans la zone primaire d'une chambre de combustion de turbo-machine

Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3808802A (en) * 1971-04-01 1974-05-07 Toyoda Chuo Kenkyusho Kk Vortex combustor
US4265615A (en) * 1978-12-11 1981-05-05 United Technologies Corporation Fuel injection system for low emission burners
US5323605A (en) * 1990-10-01 1994-06-28 General Electric Company Double dome arched combustor
US5884484A (en) * 1995-06-21 1999-03-23 Mitsubishi Heavy Industries, Ltd. Combustor having a duct with a reduced portion and an orifice plate
US6021570A (en) * 1997-11-20 2000-02-08 Caterpillar Inc. Annular one piece combustor liner
US6729141B2 (en) * 2002-07-03 2004-05-04 Elliot Energy Systems, Inc. Microturbine with auxiliary air tubes for NOx emission reduction
US20040003599A1 (en) * 2002-07-03 2004-01-08 Ingram Joe Britt Microturbine with auxiliary air tubes for NOx emission reduction
GB2441342A (en) * 2006-09-01 2008-03-05 Rolls Royce Plc Wall Elements for Gas Turbine Engine Components
GB2441342B (en) * 2006-09-01 2009-03-18 Rolls Royce Plc Wall elements with apertures for gas turbine engine components
US20110203286A1 (en) * 2010-02-22 2011-08-25 United Technologies Corporation 3d non-axisymmetric combustor liner
US8707708B2 (en) * 2010-02-22 2014-04-29 United Technologies Corporation 3D non-axisymmetric combustor liner
US10514171B2 (en) 2010-02-22 2019-12-24 United Technologies Corporation 3D non-axisymmetric combustor liner
US20120047901A1 (en) * 2010-08-16 2012-03-01 Alstom Technology Ltd. Reheat burner
US9046265B2 (en) * 2010-08-16 2015-06-02 Alstom Technology Ltd Reheat burner
US11747019B1 (en) * 2022-09-02 2023-09-05 General Electric Company Aerodynamic combustor liner design for emissions reductions

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Publication number Publication date
FR1135017A (fr) 1957-04-23
GB812201A (en) 1959-04-22
BE551418A (enrdf_load_html_response)

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