Gas turbine combustion chamber and method for manufacturing the same

Patent metadata

Field	Value
Publication number	US-9803869-B2
Application number	US-201514641833-A
Country	US
Kind code	B2
Filing date	Mar 9, 2015
Priority date	Mar 11, 2014
Publication date	Oct 31, 2017
Grant date	Oct 31, 2017

Abstract

The present invention relates to a gas-turbine combustion chamber having a head plate as well as an outer and an inner combustion chamber wall, wherein the combustion chamber is formed by segments or partial segments manufactured in one piece by means of a DLD method and welded to one another.

First claim

What is claimed is:

1. A method of manufacturing a gas-turbine combustion chamber comprising:
providing that the gas-turbine combustion chamber includes a combustion chamber head, a heat shield, an outer combustion chamber wall, and an inner combustion chamber wall;
providing partial segments of the gas-turbine combustion chamber, the partial segments each manufactured in one piece by a direct laser deposition method, the direct laser deposition method including using at least one chosen from a laser and an electron beam to melt together, layer by layer, a powdery basic material including a metallic component to produce a three-dimensional workpiece;
wherein the partial segments include first partial segments including a portion of the outer combustion chamber wall and second partial segments including a portion of the inner combustion chamber wall;
wherein one of the first partial segments and the second partial segments include a portion of the combustion chamber head, and no portion of the heat shield, manufactured as one piece with the respective portion of the inner combustion chamber wall or outer combustion chamber wall and the other of the first partial segments and the second partial segments include a portion of the heat shield, and no portion of the combustion chamber head, manufactured as one piece with the respective portion of the inner combustion chamber wall or outer combustion chamber wall;
welding the first partial segments and the second partial segments to one another to form the gas-turbine combustion chamber.

2. The method of manufacturing the gas-turbine combustion chamber in accordance with claim 1 , and further comprising providing the gas-turbine combustion chamber with a U-shaped cross-section.

3. The method of manufacturing the gas-turbine combustion chamber in accordance with claim 2 , and further comprising providing a recess in the combustion chamber head for fitting a combustion chamber seal.

4. The method of manufacturing the gas-turbine combustion chamber in accordance with claim 1 , wherein the first partial segments include the portion of the combustion chamber head, and not the portion of the heat shield, manufactured as one piece with the outer combustion chamber wall and the second partial segments include the portion of the heat shield, and not the portion of the combustion chamber head, manufactured as one piece with the inner combustion chamber wall.

5. The method of manufacturing the gas-turbine combustion chamber in accordance with claim 1 , wherein the second partial segments include the portion of the combustion chamber head, and not the portion of the heat shield, manufactured as one piece with the portion of the inner combustion chamber wall and the first partial segments include the portion of the heat shield, and not the portion of the combustion chamber head, manufactured as one piece with the outer combustion chamber wall.

Assignees

• Rolls Royce Deutschland Ltd & Co Kg

Inventors

• Clemen Carsten
• Gerendás Miklós
• Ebel Michael
• Penz Stefan

Classifications

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R2900/00018

  Manufacturing combustion chamber liners or subparts · CPC title

• F23R3/60 Primary

  Support structures; Attaching or mounting means · CPC title