Sector airflow variable geometry combustor

• US 4,720,970 A
• Filed: 11/05/1982
• Issued: 01/26/1988
• Est. Priority Date: 11/05/1982
• Status: Expired due to Fees

• Current Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Original Assignee: United States Of America As Represented By The Secretary Of The Air Force
• Inventors: Hopkins, Kenneth N., Hudson, Dale A.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): THORPE, TIMOTHY S
• Application Number:
  US06/439,492
• Time in Patent Office: 1,908 Days
• Field of Search: 60/39.27, 60/39.29, 60/39.37, 60/39.36, 60/724
• US Class Current: 60/804
• CPC Class Codes: F02C 3/14 characterised by the arrangement of the combustion chamber in the plant combustion chambers per se F23R; F02C3/205 takes precedence
• CPC Class Codes: F02K 3/10 by after-burners F02K3/105 takes precedence
• CPC Class Codes: F23R 3/10 for primary air F23R3/06, F23R3/045 take precedence
• CPC Class Codes: F23R 3/26 Controlling the air flow
• CPC Class Codes: F23R 3/346 for staged combustion

Abstract

An improved annular combustor having a plurality of annularly disposed fuel nozzles for supplying fuel to the combustor dome, and a structure defining a dome plenum adjacent each said fuel nozzle is provided, wherein means in the form of partitions or walls are included to define a sector(s) of said plenum including a portion of said fuel nozzles for airflow control by a valve means controlling airflow through said sector(s) only, the remainder of said dome plenum annulus having no airflow valve control means; said sector(s) defining means may protrude into said combustor primary zone to define a region thereof for controlled burning of fuel supplied by the fuel nozzles included in said sector.

Claims

1. A combustor, comprising:

a. a plurality of annularly disposed fuel nozzles for supplying fuel for combustion;

b. means defining an annularly-shaped combustion zone near said fuel nozzles;

c. means defining an annularly-shaped air plenum surrounding said fuel nozzles and having a plurality of openings near said fuel nozzles for supplying air for fuel combustion in said combustion zone;

d. wall means separating a predetermined angular sector of said annular air plenum from the remainder thereof, said angular sector including a predetermined portion of said plurality of fuel nozzles, whereby the airflow within said plenum to said predetermined portion of said fuel nozzles is isolated from the airflow to the remaining fuel nozzles of said combustor not within said sector; and

e. valve means for controlling the flow of air only through said sector.

2. The combustor as recited in claim 1 wherein said sector includes at least one fuel nozzle but less than all of said fuel nozzles included in said combustor.

3. The combustor as recited in claim 1 wherein said wall means protrudes into said combustion zone and separates that angular portion of said combustion zone adjacent said sector from the remainder of said combustion zone.

4. A combustor, comprising:

a. a plurality of annularly disposed fuel nozzles for supplying fuel for combustion;

b. means defining an annularly-shaped combustion zone near said fuel nozzles;

c. means defining an annularly-shaped air plenum surrounding said fuel nozzles and having a plurality of openings near said fuel nozzles for supplying air for fuel combustion in said combustion zone;

d. wall means within said plenum defining a plurality of angular sectors of said annular plenum, each of said sectors including a predetermined portion of said plurality of said fuel nozzles and said air supply openings; and

e. valve means for controlling the flow of air through only a portion of said sectors.

5. A gas turbine engine plant including a compressor, turbine and combustor, wherein said combustor comprises:

a. a plurality of annularly disposed fuel nozzles for supplying fuel for combustion;

b. means defining an annularly-shaped combustion zone near said fuel nozzles;

c. means defining an annularly-shaped air plenum surrounding said fuel nozzles and having a plurality of openings near said fuel nozzles for supplying air for fuel combustion in said combustion zone;

d. wall means separating a predetermined angular sector of said annular air plenum from the remainder thereof, said angular sector including a predetermined portion of said plurality of fuel nozzles, whereby the airflow within said plenum to said predetermined portion of said fuel nozzles is isolated from the airflow to the remaining fuel nozzles of said combustor not within said sector; and

e. valve means for controlling the flow of air only through said sector.