Angled radial fuel/air delivery system for combustor

Patent metadata

Field	Value
Publication number	US-10060629-B2
Application number	US-201514627709-A
Country	US
Kind code	B2
Filing date	Feb 20, 2015
Priority date	Feb 20, 2015
Publication date	Aug 28, 2018
Grant date	Aug 28, 2018

Abstract

A combustor is provided. The combustor may comprise an axial fuel delivery system, and a radial fuel delivery system aft of the axial fuel delivery system. The radial fuel delivery system may be configured to direct fuel at least partially towards the axial fuel delivery system. A radial fuel delivery system is also provided. The system may comprise a combustor including a combustor liner, a mixer coupled to the combustor liner, and a nozzle disposed within the mixer, wherein the mixer and the nozzle are configured to direct fuel in a direction at least partially forward.

First claim

What is claimed is:

1. An annular combustor, comprising:
a combustor liner defining a combustion chamber;
an axial fuel delivery system located forward the combustion chamber, wherein the axial fuel delivery system delivers a first fuel into the combustion chamber in a gas flow direction, wherein the gas flow direction is a direction of compressed gas traveling axially through the combustion chamber; and
a radial fuel delivery system aft of the axial fuel delivery system, the radial fuel delivery system comprising:
a mixer comprising a bluff body, wherein a mouth of the mixer is coupled to an opening in the combustor liner, and wherein the bluff body extends from an inner wall of the mixer and spans the mouth of the mixer, and
a nozzle in a cavity defined by the bluff body and the mixer, wherein the nozzle delivers a second fuel into the cavity to form a mixture of the second fuel and air in the cavity, and wherein the nozzle is oriented at an angle of between 5 degrees and 85 degrees relative to the gas flow direction and directs the second fuel into the combustion chamber at least partially in an upstream direction relative to the gas flow direction, and wherein the first fuel and the second fuel are ignited in the combustion chamber,

wherein the radial fuel delivery system extends at least partially though the combustor liner, and wherein the radial fuel delivery system is configured to direct the mixture of the second fuel and air over the bluff body to increase a mixing of the second fuel and air upon entering the combustion chamber.

2. The annular combustor of claim 1 , wherein the radial fuel delivery system is configured to direct the mixture of the second fuel and air into the combustion chamber at an axial angle between 5 degrees and 85 degrees relative to the combustor liner.

3. The annular combustor of claim 1 , wherein the radial fuel delivery system is configured to direct the mixture of the second fuel and air into the combustion chamber at an axial angle between 15 degrees and 75 degrees relative to the combustor liner.

4. The annular combustor of claim 1 , further comprising a plurality of axial fuel delivery systems having between one and three radial fuel delivery systems for each axial fuel delivery system.

5. A gas turbine engine, comprising:
a compressor;
an annular combustor aft of the compressor, the annular combustor comprising a combustor liner disposed radially outward of a combustion chamber;
an axial fuel delivery system located forward the combustion chamber, wherein the axial fuel delivery system delivers a first fuel into the combustion chamber in a gas flow direction, and wherein the gas flow direction is a direction of compressed gas traveling axially through the annular combustor; and
a radial fuel delivery system downstream of the axial fuel delivery system, the radial fuel delivery system comprising:
a mixer comprising a bluff body, wherein a mouth of the mixer is coupled to an opening in the combustor liner, and wherein the bluff body spans the mouth of the mixer, and
a nozzle in a cavity defined by the mixer, wherein the nozzle delivers a second fuel into the cavity, and wherein the nozzle is oriented at an angle of between 5 degrees and 85 degrees relative to the gas flow direction, and wherein the radial fuel delivery system is configured to direct the second fuel into the combustion chamber at least partially in an upstream direction, and wherein the first fuel and the second fuel are ignited in the combustion chamber,

wherein the radial fuel delivery system extends at least partially through the combustor liner, and wherein the radial fuel delivery system is configured to direct a mixture of the second fuel and air over the bluff body to increase a mixing of the second fuel and air upon entering the combustion chamber.

6. The gas turbine engine of claim 5 , wherein the radial fuel delivery system is configured to direct the second fuel into the combustion chamber at an angle between 5 degrees and 85 degrees relative to the combustor liner.

7. The gas turbine engine of claim 5 , wherein the radial fuel delivery system is configured to direct the second fuel into the combustion chamber at an angle between 15 degrees and 75 degrees relative to the combustor liner.

8. The gas turbine engine of claim 5 , wherein the annular combustor further comprises a plurality of axial fuel delivery systems having at least one to three radial fuel delivery systems for each axial fuel delivery system.

9. A radial fuel delivery system, comprising:
an annular combustor comprising a combustor liner defining a combustion chamber;
a mixer coupled to the combustor liner, the mixer comprising a bluff body, wherein a mouth of the mixer is located in an opening in the combustor liner, and wherein the bluff body extends from an inner wall of the mixer and spans the mouth of the mixer; and
a nozzle disposed within a cavity defined by the mixer, wherein the mixer and the nozzle are configured to direct fuel into the combustion chamber at least partially in an upstream direction relative to an axial gas flow through the combustion chamber, wherein the fuel is ignited in the combustion chamber, and wherein at least one of the nozzle or the inner wall of the mixer is oriented at an angle of between 5 degrees and 85 degrees relative to the combustor liner,
wherein the mixer and the nozzle are configured to direct a mixture of the fuel and air over the bluff body to increase a mixing of the fuel and air upon entering the combustion chamber.

10. The radial fuel delivery system of claim 9 , wherein the mixer and the nozzle are configured to deliver the mixture of the fuel and air into the combustion chamber at a negative angle relative to the axial gas flow through the combustion chamber.

11. The radial fuel delivery system of claim 9 , wherein the radial fuel delivery system is configured to direct the mixture of the fuel and air into the combustion chamber at an angle between 5 degrees and 85 degrees relative to the axial gas flow through the combustion chamber.

12. The radial fuel delivery system of claim 9 , wherein the radial fuel delivery system is configured to direct the mixture of the fuel and air into the combustion chamber at an angle between 15 degrees and 75 degrees relative to the axial gas flow through the combustion chamber.

13. The radial fuel delivery system of claim 9 , wherein the mixer is disposed at least partially through the combustor liner.

14. The radial fuel delivery system of claim 9 , wherein the nozzle is oriented at an acute angle relative to the combustor liner.

Assignees

• United Technologies Corp

Inventors

• Kim Wookyung
• Dai Zhongtao
• Kopp-Vaughan Kristin

Classifications

• F23R3/283

  Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances · CPC title

• F23R3/286 Primary

  having fuel-air premixing devices (F23R3/30 takes precedence) · CPC title

• F23R3/28 Primary

  characterised by the fuel supply (burners F23D) · CPC title

• F23R3/50

  Combustion chambers comprising an annular flame tube within an annular casing (toroidal combustion chambers F23R3/52) · CPC title

• F23R3/346

  for staged combustion · CPC title