COMBUSTION CHAMBER HAVING A CERAMIC HEAT SHIELD AND SEAL

Abstract

A combustion chamber of a gas turbine having a peripheral support structure and a heat shield arranged therein. The support structure has a reduced cross-section on the downstream side and a stop element on the upstream side. There is a gap between the heat shield and the stop element to compensate for different strains and tolerances. For reduction of the cooling air consumption, a peripheral sealing groove which is open towards the heat shield and has a sealing element arranged therein is provided in the stop element, which sealing element rests against the heat shield and covers the gap.

Claims

1. A combustion chamber comprising: a combustion chamber axis, having a peripheral support structure, said peripheral support structure having a cross-sectional reduction on the a downstream side and a stop element on an upstream side, at least one ceramic heat shield, said ceramic heat shield being arranged within the peripheral support structure, on the a side facing the a combustion space, and a position of said ceramic heat shield being delimited in a direction of the combustion chamber axis by the cross-sectional reduction and the stop element, there being a gap between the ceramic heat shield and the stop element, a peripheral seal groove which is open toward the ceramic heat shield and is arranged in the stop element, and a sealing element, which bears against the ceramic heat shield and which covers the gap and is arranged in said peripheral seal groove, and an elastically preloaded spring element, which acts on the sealing element and is arranged in the stop element.

2. The combustion chamber as claimed in claim 1, wherein the peripheral support structure has a tubular design.

3. The combustion chamber as claimed in claim 1, wherein the elastically preloaded spring element is arranged in the peripheral seal groove, between a groove bottom and the sealing element.

4. The combustion chamber as claimed in claim 1 of claims 1, wherein the cross-sectional reduction is formed by a conical portion, an outer periphery of the ceramic heat shield being supported directly or indirectly on said cross-sectional reduction.

5. The combustion chamber as claimed in claim 1, wherein the ceramic heat shield is formed, in the direction of the combustion chamber axis, by at least two heat shield elements.

6. The combustion chamber as claimed in claim 1, wherein at least one heat shield element has a tubular design.

7. The combustion chamber as claimed in claim 1, wherein, at least in certain portions along the combustion chamber axis, the ceramic heat shield is formed, in a peripheral direction, by at least two heat shield elements.

8. The combustion chamber as claimed in claim lone of claims 1, wherein at least one radially acting tensioning element is arranged between the ceramic heat shield and the peripheral support structure.

9. The combustion chamber as claimed in claim 1, wherein the combustion chamber comprises a gas turbine combustion chamber.

Description

BRIEF DESCRIPTION OF THE DRAWINGS

[0023] An exemplary embodiment for a combustion chamber according to the invention is sketched in the subsequent figure.

DETAILED DESCRIPTION OF INVENTION

[0024] The combustion chamber 01 defines a combustion chamber axis and in this case first of all comprises a rotationally shaped support structure 02. Said support structure 02 has a cross-sectional reduction 03 with a conical design on the downstream side. Located opposite on the upstream side is a stop element 04 in the form of a shoulder.

[0025] Within the support structure 02, the heat shield 11 is in this example formed by three heat shield elements 12, 13. The downstream heat shield element 12 has a conical design, just like the cross-sectional reduction 03. In this example, the outer periphery of the heat shield element 12 bears against the inner side of the cross-sectional reduction 03. However, it is more advantageous if tensioning elements are present between the heat shield 11 and the support structure 02 in the region of the cross-sectional reduction 03. Direct abutment of the heat shield element 12 against the support structure 02 is thus avoided, and the centric position is simultaneously ensured even in the case of small differences in shape between the heat shield 12 and the support structure 02. In any case, the position of the heat shield 11 is thus delimited in the downstream direction. Adjacent thereto on the upstream side, the heat shield 11 is formed by two heat shield elements 13 which are divided in the peripheral direction. In order to ensure a centric position, provision is in this case made for a plurality of radially acting tensioning elements 14 to be arranged, so as to be distributed over the periphery, between the heat shield elements 13 and the support structure 02.

[0026] Furthermore, it is possible to see the arrangement of a seal groove 05 with the sealing element 06 arranged therein. In this case, the sealing element 06 bears against the heat shield element 13 and covers a gap between the heat shield 11 and the stop 04. Unnecessary consumption of cooling air is thus avoided. In order to ensure the abutment of the sealing element 06 against the heat shield 11, provision is furthermore made of an elastically preloaded spring element 07, said spring element 07 being arranged in the seal groove 05, between the groove bottom and the sealing element 06.