Gas-turbine engine combustion system

• US 6,220,015 B1
• Filed: 07/09/1999
• Issued: 04/24/2001
• Est. Priority Date: 07/11/1998
• Status: Expired due to Term

• Current Assignee: Siemens AG
• Original Assignee: Alstom Gas Turbines Limited
• Inventors: Mina, Theodors Ishaq
• Primary Examiner(s): Freay, Charles G.
• Assistant Examiner(s): Evora, Robert Z.
• Application Number:
  US09/351,193
• Time in Patent Office: 655 Days
• Field of Search: 60/393.7, 60/393.1, 417/174
• US Class Current: 60/39.37
• CPC Class Codes: F05B 2260/202 by film cooling
• CPC Class Codes: F23R 3/48 Flame tube interconnectors, e.g. cross-over tubes

Abstract

A gas-turbine engine combustion system comprises a plurality of combustors interconnected by crossfire tube assemblies adapted to pass an ignition flame from an ignited combustor to another combustor on start-up of the engine. Each crossfire tube assembly comprises a cooling air inlet for introducing air into the assembly to film-cool its inner, ignition flame-facing surface, and a cooling sleeve surrounding the crossfire tube assembly in the region in which it opens into the combustor. The cooling sleeve directs the cooling air so as to cool the outer surface of the assembly, the inside of the sleeve and the inside surface of the combustor wall adjacent the cooling sleeve.

Claims

1. A gas-turbine engine combustion system comprising:

a plurality of combustors,

a crossfire tube assembly for passing an ignition flame between adjacent combustors, each crossfire tube assembly including an end-tube for passing the ignition flame into and out of a combustor, the end-tube having an inner surface and an outer surface, and

means for feeding coolant air into the crossfire tube assembly so as to film-cool the inner surface of the end-tube,

wherein the end-tube is connected to the combustor through a sleeve which extends from a wall of the combustor to surround and overlap the end-tube over a part of its length adjacent the combustor, thereby to define an annular gap between the outer surface of the end-tube and an inner surface of the sleeve, the sleeve having inlet means for introducing coolant air into the annular gap so as to film-cool both the outer surface of the end-tube adjacent the combustor wall and the inner surface of the sleeve.

2. The gas-turbine engine combustion system according to claim 1, in which the sleeve is provided with a plurality of apertures therearound, adjacent to a point at which the sleeve is connected to the end-tube, so that air is admitted to film-cool the outer surface of the end-tube.

3. The gas-turbine engine combustion system according to claim 1, in which the end-tube is arranged so that it does not extend beyond the sleeve into the interior of the combustor.

4. The gas-turbine engine combustion system according to claim 1, in which the overlap between the sleeve and the end-tube does not extend over the entire lengthwise extent of the sleeve, whereby there is a gap between an internal surface of the combustor wall and the end-tube.

5. The gas-turbine engine combustion system according to claim 4, in which the gap as measured between the end-tube and an inner surface of the combustor wall is approximately twice the annular gap between the inner surface of the sleeve and the outer surface of the end-tube.

6. The gas-turbine engine combustion system according to claim 1, in which the sleeve is arranged such that cooling air exits from the sleeve over an inner surface of the combustor wall surrounding the sleeve.

7. The gas-turbine engine combustion system according to claim 1, in which a complete crossfire tube arrangement extending between first and second combustors comprises a central crossfire tube portion and first and second end-tubes extending from the first and second combustors respectively, a first end of the central crossfire tube portion being welded into the first end-tube and a second end of the central crossfire tube portion being a push-fit into the second end-tube, cooling air being directed into an annular gap formed between an outer surface of the central crossfire tube portion and an inner surface of each end-tube to film-cool the ends of the central crossfire tube portion and the inner surfaces of the end-tubes.

10. The gas-turbine engine having a combustion system according to claim 1.

8. A gas-turbine engine combustion system in which adjacent combustors are connected by a crossfire tube assembly adapted to pass an ignition flame from an ignited combustor to another combustor, wherein each crossfire tube assembly comprises inlet means for introducing air to film-cool an inner ignition flame-facing surface of the crossfire tube assembly and cooling means surrounding the crossfire tube assembly at its connection to a combustor and adapted to film-cool an outer surface of the crossfire tube assembly, thereby creating film cooling over both inner and outer surfaces of the crossfire tube assembly.

9. The gas-turbine engine combustion system according to claim 8, in which a complete crossfire tube arrangement extending between first and second combustors comprises a central crossfire tube portion and first and second end-tubes extending from the first and second combustors respectively, a first end of the central crossfire tube portion being welded into the first end-tube and a second end of the central crossfire tube portion being a push-fit into the second end-tube, cooling air being directed into an annular gap formed between an outer surface of the central crossfire tube portion and an inner surface of each end-tube to film-cool the ends of the central crossfire tube portion and the inner surfaces of the end-tubes.