Gas turbine engine combustion chambers

• US 4,373,327 A
• Filed: 06/27/1980
• Issued: 02/15/1983
• Est. Priority Date: 07/04/1979
• Status: Expired due to Term

• Current Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce PLC (Rolls-Royce Holdings Plc)
• Inventors: Adkins, Richard C.
• Primary Examiner(s): Casaregola, Louis J.
• Application Number:
  US06/163,481
• Time in Patent Office: 963 Days
• Field of Search: 60/39.36, 60/39.37, 60/751, 415/207, 415/DIG. 1
• US Class Current: 60/39.37
• CPC Class Codes: F23R 3/10 for primary air F23R3/06, F23R3/045 take precedence

Abstract

In a gas turbine engine having a can annular combustion system, the diffusion passage between the outlet annulus of the engine compressor and the inlets to the individual combustion chambers located in an annular casing, is partially defined diffusion control housings, one of each of which is located adjacent the upstream end of the respective combustion chamber. Each control housing is wedge-like in planform and has a downstream recess to accommodate the dome-shaped head of the combustion chamber. The control housing increases in circumferential width and radial height in the downstream direction to reduce the diffuser area ratio. Scoops can be provided to guide primary and dilution air into each combustion chamber.

Claims

1. A gas turbine engine combustion system comprising:

an annular housing defined by inner and outer annular walls;

a plurality of combustion chambers equi-spaced apart and circumferentially arranged within said annular housing, each of said combustion chambers having an upstream and a downstream end;

a diffusion passage upstream of the upstream ends of said combustion chambers, said diffusion passage including inner and outer annular walls connected respectively to said inner and outer annular walls of said annular housing, said inner and outer walls of said diffusion passage converging in an upstream direction and arranged to receive a flow of compressed air; and

a plurality of aerodynamic struts extending between said inner and outer walls of said diffusion passage, each of said struts being adjacent to and upstream of and in alignment with a respective one of said combustion chambers, each of said struts being wedge-shaped in plan form and having an upstream apex, a downstream base spaced from the upstream apex of the respective one of said combustion chambers and sidewalls extending the full height of said diffusion passage, each of said struts having a circumferential width and radial height increasing from the apex thereof in a downstream direction to the base thereof whereby said diffusion passage increases in radial height and decreases in circumferential width in a downstream direction so as to decrease diffuser area ratio.

2. A combustion system as claimed in claim 1 in which the base of each aerodynamic strut has a recess corresponding to the shape of the upstream end of the respective one of said combustion chambers, the space between the upstream end of the combustion chamber and the recess being a plenum volume arranged to receive a flow of compressed air.

3. A combustion chamber as claimed in claim 1 in which each aerodynamic strut is a load carrying strut extending between the annular housing and a radially interior structural part of the gas turbine engine in which the combustion system is located.

4. A combustion system as claimed in claim 1 in which each one of the aerodynamic struts includes at least one fluid supply line.

5. A combustion system as claimed in claim 4 in which the fluid supply line comprises a fuel supply line.

6. A combustion system as claimed in claim 1 in which each of said combustion chambers includes an air scoop arranged to direct compressed air into a selected part of the combustion chamber.

7. A combustion system as claimed in claim 6 in which each of said combustion chambers is provided with a plurality of air inlets for secondary air, and in which said air scoop for each of said combustion chambers is positioned upstream of said air inlets and arranged to guide primary compressed air into the upstream end of the respective one of said combustion chambers.

8. A combustion system as claimed in claim 6 in which each of said combustion chambers is provided with a plurality of air inlets for secondary air and a plurality of ports for dilution air, and in which said air scoop for each of said combustion chambers is positioned intermediate said secondary air inlets and said dilution ports for guiding compressed primary air into the upstream end of the respective one of said combustion chambers and for guiding secondary air through said air inlets of the respective one of said combustion chambers.