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Publication numberUS2833115 A
Publication typeGrant
Publication dateMay 6, 1958
Filing dateJan 10, 1955
Priority dateMar 5, 1953
Publication numberUS 2833115 A, US 2833115A, US-A-2833115, US2833115 A, US2833115A
InventorsJackson Squire R, John Hudson Geoffrey, Stanley Clarke John
Original AssigneeLucas Industries Ltd
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Air-jacketed annular combustion chambers for jet-propulsion engines, gas turbines or the like
US 2833115 A
Abstract  available in
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Claims  available in
Description  (OCR text may contain errors)

May 6, 1958 J. s. CLARKE ETAL 2,833,115


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

Patent Citations
Cited PatentFiling datePublication dateApplicantTitle
US2620626 *Oct 5, 1945Dec 9, 1952Alf LysholmGas turbine propulsion unit for aircraft
Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2990108 *Mar 4, 1957Jun 27, 1961Curtiss Wright CorpCompressor with annular discharge diffuser
US5134855 *Nov 8, 1990Aug 4, 1992Rolls-Royce PlcAir flow diffuser with path splitter to control fluid flow
US5279126 *Dec 18, 1992Jan 18, 1994United Technologies CorporationDiffuser-combustor
US5289685 *Nov 16, 1992Mar 1, 1994General Electric CompanyFuel supply system for a gas turbine engine
US5303542 *Nov 16, 1992Apr 19, 1994General Electric CompanyFuel supply control method for a gas turbine engine
US5335501 *Nov 16, 1992Aug 9, 1994General Electric CompanyFlow spreading diffuser
US6651439 *Jan 12, 2001Nov 25, 2003General Electric Co.Methods and apparatus for supplying air to turbine engine combustors
US6820411 *Sep 13, 2002Nov 23, 2004The Boeing CompanyCompact, lightweight high-performance lift thruster incorporating swirl-augmented oxidizer/fuel injection, mixing and combustion
US7690192May 22, 2007Apr 6, 2010Pratt & Whitney Rocketdyne, Inc.Compact, high performance swirl combustion rocket engine
US7762058Apr 17, 2007Jul 27, 2010Pratt & Whitney Rocketdyne, Inc.Ultra-compact, high performance aerovortical rocket thruster
US7762077Dec 5, 2006Jul 27, 2010Pratt & Whitney Rocketdyne, Inc.Single-stage hypersonic vehicle featuring advanced swirl combustion
US8707708 *Feb 22, 2010Apr 29, 2014United Technologies Corporation3D non-axisymmetric combustor liner
US20110203286 *Feb 22, 2010Aug 25, 2011United Technologies Corporation3d non-axisymmetric combustor liner
U.S. Classification60/751, 60/804
International ClassificationF23R3/14, F23R3/04, F23R3/10
Cooperative ClassificationF23R3/14, F23R3/045, F23R3/10
European ClassificationF23R3/14, F23R3/04B, F23R3/10