Patent
Combustion chamber construction
Harvey Michael Maclin
- 19 Dec 1972
159
TL;DR: In this paper, a combustion chamber for use in gas turbine engines is provided with a liner formed of a high temperature material, which includes a plurality of panels of the material mounted by means of a slideable friction mounting arrangement upon a high strength structural frame.
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Abstract: A combustion chamber for use in gas turbine engines is provided with a liner formed of a high temperature material. The liner includes a plurality of panels of the material mounted by means of a slideable friction mounting arrangement upon a high strength structural frame. As a result of this mounting arrangement, the liner is substantially isolated from structural forces associated with the combustion chamber, while the frame is substantially isolated from thermal stresses associated with the liner. Means are provided for positioning and securing individual liner panels in the circumferential, axial, and radial directions with respect to the frame as well as circumferentially with respect to other liner panels. The individual liner panels may be easily removed for repair or replacement without disassembling the frame and associated components. For the purpose of cooling, a cooling fluid is passed into a plenum to cool the radially outward side of the panels by convection. Means are also provided for directing the same fluid from the plenum to the liner inner surfaces in a cooling film.
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Citations
Patent
Low emissions combustor
Joseph Douglas Monty,Thomas G. Hill,Jacob Hoffman +2 more
- 28 Mar 1990
TL;DR: In this article, a combustor effective for reducing exhaust emissions is disclosed, which includes first and second liners defining a primary combustion zone, and a plurality of circumferentially spaced carburetors.
137
Patent
Removable combustor liner for gas turbine engine combustor
Anthony Pidcock,Stephen Mark Cooper,Peter Fry +2 more
- 06 Jan 1995
TL;DR: A gas turbine engine combustor 20 has a wall structure including an outer wall 24 having a plurality of wall elements 26 attached thereto, each wall element 26 has a flange 27 around its periphery which defines a chamber 28 between each wall elements and the outer wall.
92
Patent
Combustor liner support assembly
Ely E. Halila
- 08 Feb 1993
TL;DR: A support assembly for a gas turbine engine combustor includes an annular frame having a plurality of circumferentially spaced apart tenons, and a combustor liner disposed coaxially with the frame and including a plurality for radially and tangentially supporting the liner to the frame while allowing unrestrained differential thermal radial movement there between as discussed by the authors.
Patent
Coated articles and method for the prevention of fuel thermal degradation deposits
George Albert Coffinberry,John Frederick Ackerman +1 more
- 12 Mar 1997
TL;DR: In this article, the surface for contact with a hot hydrocarbon fluid is a metal oxide, amorphous glass or metal fluoride diffusion barrier material coated on a metal substrate, and the metal oxide is deposited by chemical vapor deposition, e.g., by effusive CVD of an organometallic compound on the surface without the use of carrier gas, without pre-oxidation of the surface and without thermal decomposition of the diffusion barrier coating material.
80
Patent
Arrangement of heat resistant tiles for a gas turbine engine combustor
Lance Peter Bell,Neil Gater,Anthony Pidcock,Desmond Close,Simon Cross +4 more
- 23 Feb 1995
TL;DR: In this article, a plurality of heat resistant tiles are provided which combine to form an internal liner around the walls of an annular combustor, and the tiles are attached to the combustor in such a manner that at least one edge of the tiles is clamped against the combustors by an overlapping portion of a neighboring tile.
69
References
Patent
Means for supporting the downstream end of a combustion chamber in a gas turbine engine
Alan Ormerod,Arthur Selwyn Kay +1 more
- 09 Sep 1963
TL;DR: In this paper, the downstream end of a gas turbine engine flame tube is supported by a ring or rings 7 of U-shaped cross-section having a first limb 8 secured to the flame tube and a second limb 9 slidable in a groove 10 in the turbine casing.
40
Patent
Combustion apparatus, e. g. for a gas turbine engine
Smith Ian
- 28 Mar 1966
TL;DR: In this paper, the wall of a gas turbine engine is made of compressed layers of nickel alloy mesh to form cooling air pores, whose maximum diameter does not exceed 400 microns and is preferably in the range 5 to 300 microns.
33
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