US2833115A - Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like - Google Patents

Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like Download PDF

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Publication number
US2833115A
US2833115A US480955A US48095555A US2833115A US 2833115 A US2833115 A US 2833115A US 480955 A US480955 A US 480955A US 48095555 A US48095555 A US 48095555A US 2833115 A US2833115 A US 2833115A
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United States
Prior art keywords
air
jet
annular combustion
combustion chambers
gas turbines
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Expired - Lifetime
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US480955A
Inventor
Clarke John Stanley
Squire R Jackson
Hudson Geoffrey John
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ZF International UK Ltd
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Lucas Industries Ltd
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Priority claimed from GB612653A external-priority patent/GB739093A/en
Application filed by Lucas Industries Ltd filed Critical Lucas Industries Ltd
Priority to US480955A priority Critical patent/US2833115A/en
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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
    • 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
    • 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
    • F23R3/045—Air inlet arrangements using pipes
    • 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

Definitions

  • This invention relates to an annular combustion chamber for a jet propulsion engine, gas turbine, or the like, and of the type having an air jacket around both its inner and outer walls.
  • the object of the invention is to provide an improved construction whereby air supplied by a blower can be conveyed to the entrance end of the combustion chamber in a more satisfactory manner than heretofore.
  • the invention comprises a combustion chamber having combined with its entrance end a hollow annular nose piece shaped to direct air from an annular air entrance to each of the air jackets, and having within the nose piece a plurality of equi-spaced air scoops adapted to gather air from the passage leading to either air jacket and discharge it at a plurality of positions in the entrance end of the combustion chamber.
  • Figure l is a longitudinal section illustrating diagrammatically an annular combustion chamber provided with the invention.
  • Figure 2 is a fragmentary sectional end view on the line 2--2, Figure 1.
  • Figure 3 is a fragmentary cross sectional view taken on the line 3-3, Figure 1.
  • the annular combustion chamber there shown is constructed from sheet metal. Its outer and inner cylindrical walls, a, b consist of overlapping sections of corrugated form.
  • the combustion chamber is surrounded by outer and inner air jackets c, d.
  • the entrance end of the combustion chamber is wholly or partially closed by an annular end wall e on which are mounted the liquid fuel nozzles 1, these being equispaced on a circle which lies centrally between the outer and inner walls.
  • an air entrance g containing air swirling vanes h is provided around each nozzle.
  • the end wall is constructed 2,833,l l5 Patented May 6, 1958 from a series of segments each shaped to form a conical cavity around each nozzle.
  • a hollow annular nose piece i which together with a surrounding annular hood j forms a pair of passages k, m respectively leading from an annular entrance n to the outer and inner air jackets, the outer one of these passages being preferably situated in line with the outer air jacket 0.
  • each scoop at its entrance end projects into the air passage m leading to the inner air jackets, and the other end is connected to the corresponding air entrance orifice g in the end wall of the combustion chamber.
  • a plurality of guide vanes p is provided in each of the scoops.
  • the combustion zones associated with the burner nozzles can be supplied with the required primary combustion air in a manner which ensures uniform combustion in each of such zones. Additional air is supplied from the jackets through suitably arranged apertures in the walls of the combustion chamber, as for example, through short ducts q.
  • An annular combustion chamber having air jackets around its inner and outer walls, and having in combination a plurality of liquid fuel nozzles mounted in equispaced relationship and circular formation around one end of the chamber with the axes of the nozzles lying centrally between the inner and outer walls of the s chamber, air-swirling means surrounding each nozzle, a
  • hollow annular nose piece extending from the said end of the chamber, and shaped to direct air to the air jackets, an annular air entrance situated adjacent to the outer end of the nose piece, an annular hood surrounding the nose piece and forming therewith air passages leading from the air entrance to the air jackets, and a plurality of air scops situated in equi-spaced positions within the nose piece and leading from one of the air passages to the air swirling means around the fuel nozzles.
  • An annular combustion chamber according to claim 1 and having a plurality of guide vanes in each air scoop.

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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)

Description

May 6, 1958 J. s. CLARKE ETAL 2,833,115
AIRJACKETED ANNULAR COMBUSTION CHAMBERS FOR JET-PROPULSION ENGINES, GAS
TURBINES OR THE LIKE Filed Jan. 10, 1955 Zrzvzit0ns 6 5. Giulia?- 5.E.JCZLC K-SOR/ United States Patent AIR-JACKETED ANNULAR COMBUSTION CHAlVI- BERS FUR JET-PROPULSION ENGINES, GAS TURBINE GK THE LIKE John Stanley Clarke, Blacko, near Nelson, and Squire R. Jackson and Geoffrey John Hudson, Burnley, England, assignors to Joseph Lucas (Industries) Limited, Birmingham, England Application January 10, 1955, Serial No. 480,955
2 Claims. (Cl. 6039.65)
This invention relates to an annular combustion chamber for a jet propulsion engine, gas turbine, or the like, and of the type having an air jacket around both its inner and outer walls.
The object of the invention is to provide an improved construction whereby air supplied by a blower can be conveyed to the entrance end of the combustion chamber in a more satisfactory manner than heretofore.
The invention comprises a combustion chamber having combined with its entrance end a hollow annular nose piece shaped to direct air from an annular air entrance to each of the air jackets, and having within the nose piece a plurality of equi-spaced air scoops adapted to gather air from the passage leading to either air jacket and discharge it at a plurality of positions in the entrance end of the combustion chamber.
In the accompanying drawings, Figure l is a longitudinal section illustrating diagrammatically an annular combustion chamber provided with the invention. Figure 2 is a fragmentary sectional end view on the line 2--2, Figure 1. Figure 3 is a fragmentary cross sectional view taken on the line 3-3, Figure 1.
Referring to the drawings, the annular combustion chamber there shown is constructed from sheet metal. Its outer and inner cylindrical walls, a, b consist of overlapping sections of corrugated form. The combustion chamber is surrounded by outer and inner air jackets c, d. The entrance end of the combustion chamber is wholly or partially closed by an annular end wall e on which are mounted the liquid fuel nozzles 1, these being equispaced on a circle which lies centrally between the outer and inner walls. Around each nozzle is provided an air entrance g containing air swirling vanes h. Preferably and as shown in Figure 1, the end wall is constructed 2,833,l l5 Patented May 6, 1958 from a series of segments each shaped to form a conical cavity around each nozzle. At the said end of the combustion chamber is formed or secured a hollow annular nose piece i which together with a surrounding annular hood j forms a pair of passages k, m respectively leading from an annular entrance n to the outer and inner air jackets, the outer one of these passages being preferably situated in line with the outer air jacket 0.
In the said nose piece are secured a plurality of equispaced tubular scoops 0. Each scoop at its entrance end projects into the air passage m leading to the inner air jackets, and the other end is connected to the corresponding air entrance orifice g in the end wall of the combustion chamber. Preferably in each of the scoops is provided a plurality of guide vanes p.
By this invention the combustion zones associated with the burner nozzles can be supplied with the required primary combustion air in a manner which ensures uniform combustion in each of such zones. Additional air is supplied from the jackets through suitably arranged apertures in the walls of the combustion chamber, as for example, through short ducts q.
Having thus described our invention what we claim as new and desire to secure by Letters Patent is:
1. An annular combustion chamber having air jackets around its inner and outer walls, and having in combination a plurality of liquid fuel nozzles mounted in equispaced relationship and circular formation around one end of the chamber with the axes of the nozzles lying centrally between the inner and outer walls of the s chamber, air-swirling means surrounding each nozzle, a
hollow annular nose piece extending from the said end of the chamber, and shaped to direct air to the air jackets, an annular air entrance situated adjacent to the outer end of the nose piece, an annular hood surrounding the nose piece and forming therewith air passages leading from the air entrance to the air jackets, and a plurality of air scops situated in equi-spaced positions within the nose piece and leading from one of the air passages to the air swirling means around the fuel nozzles.
2. An annular combustion chamber according to claim 1, and having a plurality of guide vanes in each air scoop.
References Cited in the file of this patent UNITED STATES PATENTS 2,620,626 Lysholm Dec. 9, 1952
US480955A 1953-03-05 1955-01-10 Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like Expired - Lifetime US2833115A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US480955A US2833115A (en) 1953-03-05 1955-01-10 Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB612653A GB739093A (en) 1953-03-05 1953-03-05 Combustion chambers for jet-propulsion engines, gas turbines or other prime movers
US480955A US2833115A (en) 1953-03-05 1955-01-10 Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like

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Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990108A (en) * 1957-03-04 1961-06-27 Curtiss Wright Corp Compressor with annular discharge diffuser
US5134855A (en) * 1989-12-15 1992-08-04 Rolls-Royce Plc Air flow diffuser with path splitter to control fluid flow
US5279126A (en) * 1992-12-18 1994-01-18 United Technologies Corporation Diffuser-combustor
US5289685A (en) * 1992-11-16 1994-03-01 General Electric Company Fuel supply system for a gas turbine engine
US5303542A (en) * 1992-11-16 1994-04-19 General Electric Company Fuel supply control method for a gas turbine engine
US5335501A (en) * 1992-11-16 1994-08-09 General Electric Company Flow spreading diffuser
US6651439B2 (en) * 2001-01-12 2003-11-25 General Electric Co. Methods and apparatus for supplying air to turbine engine combustors
US20040050056A1 (en) * 2002-09-13 2004-03-18 Pederson Robert J. Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US20080128547A1 (en) * 2006-12-05 2008-06-05 Pratt & Whitney Rocketdyne, Inc. Two-stage hypersonic vehicle featuring advanced swirl combustion
US20080256924A1 (en) * 2007-04-17 2008-10-23 Pratt & Whitney Rocketdyne, Inc. Ultra-compact, high performance aerovortical rocket thruster
US20080256925A1 (en) * 2007-04-17 2008-10-23 Pratt & Whitney Rocketdyne, Inc. Compact, high performance swirl combustion rocket engine
US20080283677A1 (en) * 2006-12-05 2008-11-20 Pratt & Whitney Rocketdyne, Inc. Single-stage hypersonic vehicle featuring advanced swirl combustion
US20110203286A1 (en) * 2010-02-22 2011-08-25 United Technologies Corporation 3d non-axisymmetric combustor liner

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2620626A (en) * 1944-09-01 1952-12-09 Lysholm Alf Gas turbine propulsion unit for aircraft

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2620626A (en) * 1944-09-01 1952-12-09 Lysholm Alf Gas turbine propulsion unit for aircraft

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2990108A (en) * 1957-03-04 1961-06-27 Curtiss Wright Corp Compressor with annular discharge diffuser
US5134855A (en) * 1989-12-15 1992-08-04 Rolls-Royce Plc Air flow diffuser with path splitter to control fluid flow
US5289685A (en) * 1992-11-16 1994-03-01 General Electric Company Fuel supply system for a gas turbine engine
US5303542A (en) * 1992-11-16 1994-04-19 General Electric Company Fuel supply control method for a gas turbine engine
US5335501A (en) * 1992-11-16 1994-08-09 General Electric Company Flow spreading diffuser
US5279126A (en) * 1992-12-18 1994-01-18 United Technologies Corporation Diffuser-combustor
US6651439B2 (en) * 2001-01-12 2003-11-25 General Electric Co. Methods and apparatus for supplying air to turbine engine combustors
US6820411B2 (en) * 2002-09-13 2004-11-23 The Boeing Company Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US20040050056A1 (en) * 2002-09-13 2004-03-18 Pederson Robert J. Compact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US20080128547A1 (en) * 2006-12-05 2008-06-05 Pratt & Whitney Rocketdyne, Inc. Two-stage hypersonic vehicle featuring advanced swirl combustion
US20080283677A1 (en) * 2006-12-05 2008-11-20 Pratt & Whitney Rocketdyne, Inc. Single-stage hypersonic vehicle featuring advanced swirl combustion
US7762077B2 (en) 2006-12-05 2010-07-27 Pratt & Whitney Rocketdyne, Inc. Single-stage hypersonic vehicle featuring advanced swirl combustion
US20080256924A1 (en) * 2007-04-17 2008-10-23 Pratt & Whitney Rocketdyne, Inc. Ultra-compact, high performance aerovortical rocket thruster
US20080256925A1 (en) * 2007-04-17 2008-10-23 Pratt & Whitney Rocketdyne, Inc. Compact, high performance swirl combustion rocket engine
US7690192B2 (en) 2007-04-17 2010-04-06 Pratt & Whitney Rocketdyne, Inc. Compact, high performance swirl combustion rocket engine
US7762058B2 (en) 2007-04-17 2010-07-27 Pratt & Whitney Rocketdyne, Inc. Ultra-compact, high performance aerovortical rocket thruster
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

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