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Publication numberUS2511432 A
Publication typeGrant
Publication dateJun 13, 1950
Filing dateFeb 13, 1946
Priority dateFeb 20, 1945
Publication numberUS 2511432 A, US 2511432A, US-A-2511432, US2511432 A, US2511432A
InventorsRobert Feilden Geoffrey Bertra
Original AssigneePower Jets Res & Dev Ltd
Export CitationBiBTeX, EndNote, RefMan
External Links: USPTO, USPTO Assignment, Espacenet
Support for multiple flame tubes
US 2511432 A
Abstract  available in
Previous page
Next page
Claims  available in
Description  (OCR text may contain errors)

June 13, 1950 e. B. R. FEILDEN 1943?;

SUPPORT FOR MULTIPLE FLAME TUBES Filed Feb. 13, 1946 3 Sheets-Sheet l Fig. i.

{bio/new June w, i950 G. B. R. FEILDEN 2,511,432

SUPPORT FOR MULTIPLE FLAME TUBES Filed Feb. 13, 1946 3 Sheets-Sheet 2 Fig.2

Fig. 5.

4144/ 1485 o/Wmy June 1950 G. B. R. FEILDEN SUPPORT FOR MULTIPLE FLAME mass 3 Sheets-Sheet 3 Filed Feb. 13, 1946 Z14 Mar/19w Patented June 13, 1950 UNITED STATES SUPPORT FOR MULTIPLE FLAME TUBES Geoffrey Bertram Robert Feilden, Lutterworth, near Rugby, England, assignor to Power Jets (Research and Development) Limited, London,

England Application February 13, 1946, Serial No.'647,381 In Great Britain February 20, 1945 2 Claims. (01. 60-44) 1 v This invention relates to combustion apparatus and more particularly to apparatus for inclusion in a gas turbine comprising a compressor, combustion apparatus supplied therefrom and a turbinewhich supplies the compressor with mea chanical power. Among the many arrangements proposed for such machines are designs in which the combustion apparatus lies between the compressor and the turbine occupying a certain proportion of the axial length of the machine. In such designs it is necessary to allow for expansions and deformations primarily due to thermal conditions but also due sometimes to stress conditions. It therefore becomes desirable to contrive the combustion apparatus in such a way that it not only fulfils its functions as such with a high degree of efliciency and with the lowest possible pressure loss in the gases passing through it, but also to allow for changes of dimension each of the said pair of members comprises a curved arm which partly envelops the flame tube. Each pair may consequently together form an approximately semi-circular shaped element which partially encircles the flame tube, and the'attachment to the aircasing may be by means of a link connected to the common ends of the arms. This device supports the flame tube with certain freedom for lengthwise movement either as a whole or locally, and a third attachment is provided preferably at the outlet of the flame tube and in this case to the structure in the vicinity of the turbine nozzle ring. At the other end of the flame tube an arrangement is preferably provided whereby the wall of the flame tube converges to a burner for fuel injection which is mounted in the structure of the machine and extends slightly in the axial sense into the flame tube, and the apex of the latter surrounds the either overall or locally. Especially in the case go burner with freedom for axial motion and preferof an aero engine gas turbine lightness is a primary consideration, whilst the desirability of freedom from trouble and accessibility for inspection or replacement is evident. The invention ably with a slight radial clearance through which some of the airflow can pass.

In a modified form of embodiment as applied to a circular series of flame tubes, one of a pair seeks to satisfy these requiremnts. Its applica- 85 of members supporting one flame tube is contion is not, however, limited to cases in which the combustion apparatus lies between the compressor and the turbine though such application is at present preferred. The invention may also nected to or made rigid with the adjacent member of the pair of members supporting the immediately adjacent flame tube. In this case the two members s connected may be formed by a be applied to engines of the type in which the 0 V-shaped strut located between adjacent flame combustion apparatus extends beyondgthe turbine and there. is reversal of direction of flow of the working gas.

The invention is concerned with the constructubes, each leg being pivotally attached to the casing so as to pivot in the axial direction, and the walls of the adjacent flame tubes are connected together by a common bracket which is tion, arrangement and mounting of flame tubes, itself pivotally attached to the strut.

that is to say, chambers in which combustion is to take place and into which fuel is injected and into and through which the working gas passes. Desirably, though not essentially, the invention The above and other features of the invention will be better understood from the description given hereinunder by way of example and made with reference to the accompanying drawings is intended to be applied to arrangements in 40 in which: a

which fiam'e tubes being in themselves in the main cylindrical bodies are contained as a circular series centred on the axis of the machine within an aniiular aircasing which receives the Figure 1 is a sectional elevation of one form of a gas turbine power unit to which the invention may be applied;

Figure 2 is an enlarged view of a flamev tube air from the compressor, the flame tubes being 4 with one form of mounting;

led at their outlets to the nozzle of the turbine.

According to one feature of the invention, combustion apparatus for a continuous combustion engine includes a flame tube supported within an Figure 3 is a sectional view on the line III-III of Figure 2;

Figure 4 is an enlarged view of a flame tube with a second form of mounting;

aircasing by support means comprising at least Figure 5 is a sectional view on the line V-V one pair of support members connected to said tube at diametrically opposite locations thereof and to said casing by means adapted to deflect in a direction parallel to the axis of said tube.

According to a further feature of the invention 68 of Figure 4.

In Figure 1 a gas turbine plant comprises a compressor having a multistage axial flow section I and a centrifugal final stage 2 accommodated in a unitary casing 3, the general form of the axial flow section being convergent to its outlet to the centrifugal stage; a combustion system comprising an annular aircasing formed by inner and outer sheet metal walls 4, encloslngQn annularly arranged series of flame tubes 6 and a turbine I exhausting to a propulsive jet duct 8 and driving the compressor through a shaft 9. In this arrangement the compressor supplies air both through and around the flame tubes 6 but combustion of fuel which is supplied by burners l4 takes place only within the tubes 6., The entire power plant is assumed to be symmetrical about its horizontal centre line passing through the shaft 9. i

The compressor 2 has a circular series of axially directed outlets 2|. On a circle within this series there is attached to the compressor wall II the inner wall 4 of the annular aircasing which extends from the compressor 2 to the inner margin of a continuous entry turbine nozzle ring 22. To the periphery of the compressor casing (outside the series of outlets 2|) is likewise attached the edge of the outer aircasing wall 5 which extends to the outer margin of the nozzle 22, these two walls 4, 5 both being appropriately pressureresistant. The inner chamber enclosed by the air-casing wall 4 is maintained under pressure by air supplied through a pipe I! from a convenient point in the plant, thus compensating for the external pressure in the aircasing. The outer wall, or a section of it, may be arranged to be displaceable for internal inspection by being moved bodily in an axial or radial direction. Within the aircasing so formed a circular series of flame tubes 6 is provided half as numerous as the compressor outlets 2|, and each flame tube converges at its downstream end to a segmental outlet 23 corresponding to a segment of the turbine nozzle 22 and attached to the structure in the region thereof by a plate 24. At the other ends of the flame tubes 6 they are also convergent conically to a comparatively small circular margin in which a sleeve or bush I9 is fixed, this being intended to surround the inwardly extending burner l0.

The flame tube 6 is mounted in the aircasing 4, 5 by means of support members which are shown diagrammatically in Figure 1 at 20, and which are pivotably connected to the flame tube 6 and the aircasing 4, 5.

One form of flame tube mounting according to the invention is shown in detail in Figures 2 and '3 in which towards the upstream end of each flame tube 6 a virtually semi-circular supporting strut or link comprising two arms 25 is pivoted at 26 to the outside of the flame tube wall 6 on an axis which lies on a diameter of the tube and these arms have a common link 34 itself pivoted at 21 to the inner wall 4 of the aircasing, the arm 25 in normal conditions lying in a, plane approximately at right angles to the axis of the flame tube and pivotable axially. A similar structure 25A, 34A is provided towards the downstream end of the tube 6, and this may alternatively be pivoted to the outer wall 6 of the aircasing as shown in broken lines at 25B, 343, the two linkages 25, 25A, thus forming an almost parallel armed mounting system which in conjunction with the flxing 24 at the outlet end supports the flame tube 6 in all possible degrees of freediim whilst permitting, by slight angular movement, expansions or like small displacements. The upstream end of each tube 0 is enshrouded and overlapped by an air duct 24 which is branched further upstream so as to be connected to adjacent compressor outlets.

A second form of mounting is shown in Pigures 4 and 5 in which the flame tubes 4A, B, etc., are arranged in a circular series within the annular aircasing 4, 5. In this case one of the pair of support members for tube A is attached to the adjacent member of the pair of support members for tube 6B, the combined structure presenting the form of a V-shaped strut 24A, 2IB pivoted at 30A, "B respectively to the inner aircasing wall 4. and brackets 3| attached to the tubes 6A, 4B and pivoted at 32 to the V strut.

In this embodiment the flame tube 4. is free at its outlet end but is held rigidly to the inner aircasing wall 4 by a strut 32.

Although the invention has been described with reference to a centrifugal compressor it is to be understood that it may also be applied to the case of a purely axial compressor in which case segmental portions of the outlet thereof may be connected to a circular series of individual aircasings in each of which a flame tube is mounted. The supporting struts shown may instead oi being pivotably mounted be adapted to be flexible while achieving the objects of the invention.

I claim:

1. In or for a gas turbine engine, combustion apparatus comprising an air casing and a plurality of flame tubes arranged within said casing with their axes extending in the same general direction, each flame tube being supported by support means comprising a least one pair of support members each connected to said tube at substantially diametrically opposite locations thereof, the members being mounted on said casing by means adapted to deflect in a direction substantially parallel to the axis of the tube and one member of a pair of support members of one tube being attached to the immediately adjacent member of the pair of support members for an immediately adjacent tube.

2. In or for a gas turbine engine, the combustion apparatus according to claim 1 wherein the attached members are mounted on said casing by a common strut adapted to deflect in a direction substantially parallel to the axis of said tube.


REFERENCES CITED The following references are of record in the file of this patent:


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Referenced by
Citing PatentFiling datePublication dateApplicantTitle
US2627720 *Oct 8, 1948Feb 10, 1953Packard Motor Car CoCircumferentially arranged combustion chamber with arcuate walls defining an air flow path between chambers
US2676459 *May 24, 1948Apr 27, 1954Bristol Aeroplane Co LtdGas turbine engine having a continuous outer stress bearing shell and means allowing access through the shell to the combustion space of the engine
US2746246 *Sep 5, 1952May 22, 1956Alessandro ValotaAxial flow gas turbine
US2780174 *Mar 19, 1951Feb 5, 1957Solar Aircraft CoPump and power plant assembly
US2807934 *Dec 6, 1951Oct 1, 1957A V Roe Canada LtdFlame tube support for a gas turbine combustion system
US2839894 *Dec 31, 1952Jun 24, 1958Gen Motors CorpSupporting arrangement for a gas turbine combustion chamber
US2852914 *Dec 30, 1955Sep 23, 1958United Aircraft CorpCombustion chamber support means
US3481146 *Dec 28, 1967Dec 2, 1969Lucas Industries LtdCombustion apparatus for gas turbine engines
US4422288 *Mar 2, 1981Dec 27, 1983General Electric CompanyAft mounting system for combustion transition duct members
US5761898 *Aug 1, 1996Jun 9, 1998General Electric Co.Transition piece external frame support
US8322146 *Aug 22, 2008Dec 4, 2012Alstom Technology LtdTransition duct assembly
US8448444 *Feb 18, 2011May 28, 2013General Electric CompanyMethod and apparatus for mounting transition piece in combustor
US8893511 *Jun 4, 2013Nov 25, 2014General Electric CompanySystems and methods for a gas turbine combustor having a bleed duct
US20090145137 *Aug 22, 2008Jun 11, 2009Alstom Technologies, Ltd., LlcTransition duct assembly
US20120210729 *Feb 18, 2011Aug 23, 2012General Electric CompanyMethod and apparatus for mounting transition piece in combustor
US20130255273 *Jun 4, 2013Oct 3, 2013General Electric CompanySystems and Methods for Gas Turbine Combustors
U.S. Classification60/796, 60/800
International ClassificationF23R3/60, F23R3/00
Cooperative ClassificationF23R3/60
European ClassificationF23R3/60