Gas turbine combustion chamber

Patent metadata

Field	Value
Publication number	US-9377197-B2
Application number	US-201013387905-A
Country	US
Kind code	B2
Filing date	Jul 20, 2010
Priority date	Jul 31, 2009
Publication date	Jun 28, 2016
Grant date	Jun 28, 2016

Abstract

A gas turbine combustion chamber has a housing ( 1 ), a flame tube ( 2 ) received therein, and a perforated plate ( 3 ) which at least partially surrounds the latter and which is fastened at both of its end faces ( 3.1, 3.2 ) to the housing.

First claim

The invention claimed is:

1. A gas turbine combustion chamber comprising:
an outer housing portion ( 1 );
a flame tube ( 2 ) disposed within said outer housing portion;
a perforated plate ( 3 ) at least partially surrounding said flame tube ( 2 ) and having an upper end face and a lower end face, each end face being fastened, at a respective fastening point, to a respective end of said outer housing portion, said perforated plate having cooling apertures ( 4 ) at least in a primary combustion area of said flame tube for impingement cooling of the flame tube ( 2 ); and
a radial swirler ( 5 ) having an end plate ( 6 ), one of said end faces of said perforated plate being fastened to said end plate ( 6 ),
wherein said outer housing portion and said perforated plate ( 3 ) define an annular chamber therebetween configured to impinge combustion air (L) on said perforated plate ( 3 ), the annular chamber ( 1 ) being further defined by a distance between the respective fastening points, and
wherein the outer housing portion, the perforated plate ( 3 ), the respective fastening points, the end plate ( 6 ) and the radial swirler ( 5 ) are configured to cooperate with one another such that all of the combustion air is used initially to cool the flame tube ( 2 ) and then flows through the radial swirler.

2. The gas turbine combustion chamber according to claim 1 , wherein said perforated plate ( 3 ) is constructed to transmit loads of the outer housing portion ( 1 ).

3. The gas turbine combustion chamber according to claim 1 , wherein said outer housing portion ( 1 ) comprises one or more parts.

4. The gas turbine combustion chamber according to claim 1 , wherein at least one of said end faces of said perforated plate is nondetachably fastened to said outer housing portion.

5. The gas turbine combustion chamber according to claim 4 , wherein said at least one end face is nondetachably fastened by welding.

6. The gas turbine combustion chamber according to claim 1 , wherein said perforated plate ( 3 ) is formed of one or more parts.

7. The gas turbine combustion chamber according to claim 1 , wherein at least one corresponding area of said outer housing portion and of said perforated plate has substantially the same wall thickness.

8. The gas turbine combustion chamber according to claim 1 , wherein said perforated plate ( 3 ) is shaped substantially as a right circular cylinder.

9. A gas turbine comprising at least one gas turbine combustion chamber according to claim 1 .

10. The gas turbine according to claim 9 , further comprising one of a cover and a base housing and wherein said gas turbine combustion chamber comprises screw connections for connecting said gas turbine combustion chamber to one of said cover and said base housing.

11. The gas turbine combustion chamber of claim 1 , wherein at least one of said end faces of said perforated plate is fastened to said outer housing portion by one selected from the group consisting of gluing, press-fitting and riveting.

Assignees

• El Masalme Jaman
• Aschenbruck Emil
• Brinkmann Reiner
• Man Diesel & Turbo Se

Inventors

• El Masalme Jaman
• Aschenbruck Emil
• Brinkmann Reiner

Classifications

• F23R2900/03044

  Impingement cooled combustion chamber walls or subassemblies · CPC title

• F23R3/002 Primary

  Wall structures (F23R3/02 and F23R3/007 take precedence) · CPC title

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R3/04

  Air inlet arrangements · CPC title