Combustors with quench inserts

• US 9,062,884 B2
• Filed: 05/26/2011
• Issued: 06/23/2015
• Est. Priority Date: 05/26/2011
• Status: Active Grant

• Current Assignee: Honeywell International Inc.
• Original Assignee: Honeywell International Inc.
• Inventors: Rudrapatna, Nagaraja S., Frye, Lowell, Landram, William
• Primary Examiner(s): Wongwian, Phutthiwat
• Assistant Examiner(s): SUTHERLAND, STEVEN M
• Application Number:
  US13/116,897
• Publication Number:
  US 20120297778A1
• Time in Patent Office: 1,489 Days
• Field of Search: 60752-760, 607/96, 607/98
• US Class Current: 1/1
• CPC Class Codes: F23R 3/045 using pipes
• CPC Class Codes: F23R 3/06 Arrangement of apertures along the flame tube
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft
• CPC Class Codes: Y10T 29/49348 Burner, torch or metallurgical lance making

Abstract

A combustor is provided for a turbine engine. The combustor includes a first liner having a first hot side and a first cold side; a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween. The combustion chamber is configured to receive an air-fuel mixture for combustion therein. The combustor further includes an insert having a body portion extending through the first liner and terminating at a tip, the body portion configured to direct air flow into the combustion chamber. The insert further includes a cooling hole defined in the body portion and configured to direct a first portion of the air flow toward the tip as cooling air.

Claims

1. A combustor for a turbine engine, comprising:

a first liner having a first hot side and a first cold side;

a second liner having a second hot side and a second cold side, the second hot side and the first hot side forming a combustion chamber therebetween, the combustion chamber configured to receive an air-fuel mixture for combustion therein; and

an insert comprising a body portion extending through the first liner and terminating at a tip, the body portion configured to direct air flow into the combustion chamber,

the insert further including a cooling hole defined in the body portion and configured to direct a first portion of the air flow toward the tip as cooling air,

wherein the body portion has an interior surface and an exterior surface, the cooling hole extending from the interior surface to the exterior surface,

wherein the body portion is generally tubular,

wherein the first liner is a single-walled liner, and

wherein the tubular body portion has a longitudinal axis, and wherein the cooling hole extends from the interior surface to the exterior surface at an angle of less than 90° and

greater than 0°

relative to the longitudinal axis, wherein the cooling hole extends from an inlet on the interior surface to an outlet on the exterior surface, the angle being defined at the outlet relative to the external surface.

2. The combustor of claim 1, wherein the cooling hole is at least partially defined in the exterior surface of the body portion proximate to the tip.

3. The combustor of claim 1, wherein the body portion further comprises a shoulder circumscribing the body portion and abutting the first hot side, and an inlet portion coupled to the body portion and arranged relative to the first cold side such that the inlet portion and the shoulder capture the first liner therebetween to retain the insert.

4. The combustor of claim 1, wherein the combustion chamber defines a rich burn zone, a quench zone, and a lean burn zone, and the insert is configured to introduce air into the quench zone.

5. The combustor of claim 1, wherein the body portion projects into the combustion chamber.

6. The combustor of claim 1, wherein the body portion includes an inlet portion opposite the tip, the inlet portion being flared to guide air into the insert.

7. The combustor of claim 1, wherein the angle is approximately 20°

relative to the longitudinal axis.