UNKNOWN

• US 20140033723A1
• Filed: 07/22/2013
• Published: 02/06/2014
• Est. Priority Date: 08/03/2012
• Status: Active Grant

• Current Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Deutschland Limited & Company KG (Rolls-Royce Holdings Plc)
• Inventors: DOERR, Thomas, RACKWITZ, Leif, PENZ, Stefan
• Granted Patent: US 9,328,665 B2
• Time in Patent Office: Days
• US Class Current: 60/737
• CPC Class Codes: F02C 7/22 Fuel supply systems
• CPC Class Codes: F23R 3/007 constructed mainly of ceramic components
• CPC Class Codes: F23R 3/045 using pipes
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: F23R 3/60 Support structures; Attaching or mounting means

Abstract

The present invention relates to a gas-turbine combustion chamber with mixing air orifices, with a combustion chamber wall, with tiles arranged on the inside of the combustion chamber wall at a certain distance from said combustion chamber wall as well as with mixing air orifices passing through the combustion chamber wall and the tiles, characterized in that the mixing air orifices are formed by chutes which are designed tube-like and pass through the tiles, and that several chutes are formed on a mixing air wall element extending at least around part of the circumference of the combustion chamber.

Claims

1. Gas-turbine combustion chamber with mixing air orifices, with a combustion chamber wall, with tiles arranged on the inside of the combustion chamber wall at a certain distance from said combustion chamber wall as well as with mixing air orifices passing through the combustion chamber wall and the tiles, characterized in that the mixing air orifices are formed by chutes which are designed tube-like and pass through the tiles, and that several chutes are formed on a mixing air wall element extending at least around part of the circumference of the combustion chamber.

2. Gas-turbine combustion chamber in accordance with claim 1, characterized in that the mixing air wall element is designed in the form of a circular segment.

3. Gas-turbine combustion chamber in accordance with claim 1, characterized in that the mixing air wall elements are connected to adjacent tile support wall elements.

4. Gas-turbine combustion chamber in accordance with claim 3, characterized in that the mixing air wall elements are connected to the tile support wall elements by means of bolts.

5. Gas-turbine combustion chamber in accordance with claim 3, characterized in that the mixing air wall elements are connected to the tile support wall elements by a welding process.

6. Gas-turbine combustion chamber in accordance with claim 1, characterized in that the mixing air wall elements are manufactured as castings.

7. Gas-turbine combustion chamber in accordance with claim 1, characterized in that the chutes are arranged in a single row in the circumferential direction.

8. Gas-turbine combustion chamber in accordance with claim 1, characterized in that tiles are arranged on the tile support wall elements at a certain distance from said wall elements.

9. Gas-turbine combustion chamber in accordance with claim 1, characterized in that the mixing air wall elements and the tile support wall elements form rings or ring segments, each extending in the circumferential direction of the combustion chamber, said rings or ring segments being adjacently arranged in the axial direction and connected to a combustion chamber head.

10. Gas-turbine combustion chamber in accordance with claim 1, characterized in that the chutes are provided with a rounded flow-optimized inflow area.