Combustor dome heat shield

• US 4,843,825 A
• Filed: 05/16/1988
• Issued: 07/04/1989
• Est. Priority Date: 05/16/1988
• Status: Expired due to Term

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Clark, Jim A.
• Primary Examiner(s): Casaregola, Louis J.
• Assistant Examiner(s): Thorpe, Timothy S.
• Application Number:
  US07/194,354
• Time in Patent Office: 414 Days
• Field of Search: 60/756, 60/757, 60/752, 60/39.141, 60/755, 60/759, 60/747, 60/39.37
• US Class Current: 60/756
• CPC Class Codes: F05B 2260/201 by impingement of a fluid
• CPC Class Codes: F23R 3/002 Wall structures F23R3/02 and F23R3/007 take precedence
• CPC Class Codes: F23R 3/10 for primary air F23R3/06, F23R3/045 take precedence

Abstract

An annular combustor has a plurality of fuel injectors 14, each supporting a heat shield 30. Each shield has an overlap portion 42 deflecting cooling air passing between the shields, thereby avoiding a curtain of air between the flames of adjacent fuel injectors.

Claims

1. An annular combustor for a gas turbine engine comprising:

an annular combustion chamber having an inner circumference and an outer circumference;

a plurality of circumferentially spaced fuel injectors in said combustion chamber;

swirl means for introducing fuel and primary air to said combustion chamber in a swirl around the axis of each of said injectors;

at least one ignitor extending from one circumference of said combustion chamber;

an annular support dome structure for supporting said plurality of fuel injectors and for passing secondary air therethrough;

a plurality of circumferentially spaced heat shields interposed between said dome structure and said combustion chamber, each one of said heat shields secured to one of said fuel injectors; and

an overlap portion on each of said heat shields axially overlapping an adjacent heat shield, whereby secondary air passing between said heat shields is deflected away from the axial direction toward the circumferential direction.

2. A combustor as in claim 1:

said swirl means establishing a common circumferential flow direction on each radial side of said plurality of fuel injectors; and

said overlap portion of each heat shield overlapping the adjacent heat shield to deflect secondary air passing therebetween in the same circumferential direction as said common flow direction.

3. A combustor as in claim 2:

said overlap portion of each heat shield overlapping the adjacent heat shield only on one radial side of said plurality of fuel injectors.

4. A combustor as in claim 3:

said one radial side being the radial side contiguous with the circumference containing said ignitor.

5. A combustor as in claim 2:

said overlap portion of each heat shield overlapping the adjacent heat shield on both radial sides of said plurality of fuel injectors.

6. A combustor as in claim 4:

said circumference being the outer circumference.