Combustion-chamber arrangement

• US 6,725,666 B2
• Filed: 08/28/2002
• Issued: 04/27/2004
• Est. Priority Date: 08/31/2001
• Status: Expired due to Fees

• Current Assignee: Siemens AG
• Original Assignee: Siemens AG
• Inventors: Tiemann, Peter
• Primary Examiner(s): KIM, TAE JUN
• Application Number:
  US10/232,177
• Publication Number:
  US 20040011059A1
• Time in Patent Office: 608 Days
• Field of Search: 607/52, 607/53, 607/54, 607/55, 607/56, 607/57, 607/58, 607/59, 607/60, 607/98
• US Class Current: 60/798
• CPC Class Codes: F23R 3/005 Combined with pressure or heat exchangers
• CPC Class Codes: F23R 3/007 constructed mainly of ceramic components
• CPC Class Codes: F23R 3/50 Combustion chambers comprising an annular flame tube within an annular casing toroidal combustion chambers F23R3/52

Abstract

The invention relates to a combustion-chamber arrangement for gas turbines, having an annular combustion chamber connected to at least one burner and leading into a turbine space, an annular-combustion-chamber wall which defines the annular combustion chamber being of double-shell construction, and an inner shell of the annular-combustion-chamber wall being composed of lining elements releasably arranged on an outer shell of the annular-combustion-chamber wall, and a gap space through which a cooling medium can flow being formed between the inner shell and the outer shell of the annular-combustion-chamber wall. In order to develop such a combustion-chamber arrangement to the effect that it is possible to exchange individual lining elements of the inner shell of the annular-combustion-chamber wall with comparatively little outlay, it is proposed with the invention that the lining elements be of trapezoidal design having in each case a fastening structure, formed in each of the longitudinal sides and directed outward, for releasably fastening to a corresponding mating structure of an adjoining lining element and/or a supporting structure connected to the outer shell.

Claims

1. A combustion chamber arrangement for gas turbines, comprising

an annular combustion chamber wall having a double-shell construction, with an inner shell and an outer shell, with a gap space being defined by the inner shell and outer shell through which a cooling medium can flow there between,

at least one burner connected to one end of the annular combustion chamber leading into a turbine space, and

wherein the inner shell being composed of lining elements having longitudinal sides and being releasably arranged on the outer shell, wherein the lining elements are of trapezoidal design and are connected to a supporting structure of the outer shell by pushing a fastening structure into a mating structure in a direction along the longitudinal sides and wherein the lining elements having wide end faces and narrower ends faces wherein the lining elements are all arranged so as to be oriented with the wider end faces in the direction of the burner and the narrower end faces in the direction of the turbine space and wherein a longitudinal groove is arranged on the wider end face of the lining elements as further fastening structure.

2. The combustion chamber arrangement as claimed in claim 1, wherein each longitudinal side having a least one longitudinal groove with the supporting structure and fastening structure located in the longitudinal groove for maintaining the lining elements in place.

3. The combustion chamber arrangement as claimed in claim 2 further comprising second fastening structures formed in the latitudinal side of the lining elements for the releasable fixing to the outer shell.

4. The combustion chamber arrangement as claimed in claim 3, further comprising an opening arranged in the second fastening structure on a narrower end face of the liners is provided for the placement of a fastening device to further fasten the lining elements.

5. The combustion chamber arrangement as claimed in claim 1 wherein the annular combustion chamber has an axial direction and at least two lining elements are arranged in sequence one behind the other in the axial direction of the annular combustion chamber, and adjoining one another along a parting line running in the circumferential direction of the annular combustion chamber.

6. The combustion-chamber arrangement as claimed in claim 1 wherein the annular combustion chamber, in its axial orientation, is set at an angle to a machine axis defined by the axial extent of the turbine space for a machine that the combustion chamber is used upon.

7. The combustion chamber arrangement as claimed in claim 6 wherein the annular combustion chamber is subdivided in its axial extent into at least two sections which are set at different angles to the machine axis, and the lining elements extending continuously over individual sections of the annular combustion chamber in the axial direction.

8. The combustion chamber arrangement as claimed in claim 1 wherein the at least one burner comprises a plurality of axially displaceable burners.

9. A combustion chamber arrangement for gas turbines, comprising

an annular combustion chamber wall having a double-shell construction, with an inner shell and an outer shell, with a gap space being defined by the inner shell and outer shell through which a cooling medium can flow there between,

at least one burner connected to one end of the annular combustion chamber leading into a turbine space, and

wherein the inner shell being composed of lining elements having longitudinal sides and being releasably arranged on the outer shell, wherein the lining elements are of trapezoidal design and are connected to a supporting structure of the outer shell by pushing a fastening structure into a mating structure in a direction along the longitudinal sides, wherein a displacement distance on the supporting structure for changing the lining elements is less than 15 cm.