Turbine engine assembly including a rotating detonation combustor

Patent metadata

Field	Value
Publication number	US-2021190320-A1
Application number	US-202117195131-A
Country	US
Kind code	A1
Filing date	Mar 8, 2021
Priority date	Sep 15, 2017
Publication date	Jun 24, 2021
Grant date	—

Abstract

A rotating detonation combustor includes a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas and an air plenum configured to contain a volume of air. The rotating detonation combustor also includes a flow passage coupled in flow communication between the combustion chamber and the air plenum and configured to channel an airflow from the air plenum. The rotating detonation combustor also includes a fuel inlet coupled in flow communication with the flow passage and configured to channel a fuel flow into the flow passage. The flow passage includes a plurality of fuel mixing mechanisms configured to mix the airflow and the fuel flow within the combustion chamber.

First claim

1 . A rotating detonation combustor comprising:
a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas; an air plenum configured to contain a volume of air; a flow passage coupled in flow communication between said combustion chamber and said air plenum and configured to channel an airflow from said air plenum, wherein said flow passage comprises a plurality of fuel mixing mechanisms; a fuel inlet coupled in flow communication with said flow passage and configured to channel a fuel flow into said flow passage, wherein said plurality of fuel mixing mechanisms are configured to mix said airflow and said fuel flow within said combustion chamber; and a splitter at least partially positioned in said flow passage, wherein said splitter comprises a plurality of splitter fuel mixing mechanisms.

2 .- 6 . (canceled)

7 . The rotating detonation combustor in accordance with claim 1 , wherein said splitter comprises a first end that is substantially planar and an opposing second end that includes said plurality of splitter fuel mixing mechanisms.

8 . The rotating detonation combustor in accordance with claim 7 , wherein said splitter comprises a plurality of openings positioned upstream of said flow passage.

9 . A rotating detonation combustor comprising:
a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas; an air plenum configured to contain a volume of air; a first sidewall and a second sidewall that define a flow passage therebetween, said flow passage coupled in flow communication between said combustion chamber and said air plenum and configured to channel an airflow from said air plenum; an air flow splitter positioned within said flow passage between said first sidewall and said second sidewall; a plurality of fuel mixing mechanisms coupled to at least one of said splitter and said first and second sidewalls; and a plurality of fuel inlets coupled in flow communication with said flow passage and configured to channel a fuel flow into said flow passage, wherein said plurality of fuel mixing mechanisms are configured to mix said airflow and said fuel flow within said combustion chamber.

10 . The rotating detonation combustor in accordance with claim 9 , wherein said first and second sidewall include said plurality of fuel mixing mechanisms, and wherein said splitter does not include said plurality of fuel mixing mechanisms.

11 . The rotating detonation combustor in accordance with claim 9 , wherein said first and second sidewall include a first plurality of fuel mixing mechanisms of said plurality of fuel mixing mechanisms, and wherein said splitter includes a second plurality of fuel mixing mechanisms of said plurality of fuel mixing mechanisms.

12 . The rotating detonation combustor in accordance with claim 9 , wherein said splitter includes said plurality of fuel mixing mechanisms, and wherein said first and second sidewall do not include said plurality of mixing mechanisms

13 . The rotating detonation combustor in accordance with claim 9 , wherein said first sidewall includes a first plurality of fuel inlets of said plurality of fuel inlets defined therethrough and wherein said second sidewall includes a second plurality of fuel inlets of said plurality of fuel inlets defined therethrough.

14 . The rotating detonation combustor in accordance with claim 9 , wherein said plurality of fuel inlets are formed in said splitter.

15 . The rotating detonation combustor in accordance with claim 14 , wherein at least one fuel inlet of said plurality of fuel inlets is obliquely oriented with respect to a centerline of the rotating detonation chamber such that fuel is injected at an angle into said combustion chamber.

16 . A turbine engine assembly comprising:
a plurality of rotating detonation combustors, wherein each rotating detonation combustor comprises: a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas; an air plenum configured to contain a volume of air; a flow passage coupled in flow communication between said combustion chamber and said air plenum and configured to channel an airflow from said air plenum, wherein said flow passage comprises a plurality of fuel mixing mechanisms; a fuel inlet coupled in flow communication with said flow passage and configured to channel a fuel flow into said flow passage, wherein said plurality of fuel mixing mechanisms are configured to mix said airflow and said fuel flow within said combustion chamber; and a turbine coupled downstream from said plurality of rotating detonation combustors, said turbine configured to receive the flow of combustion gas, wherein each rotating detonation combustor further comprises a centerline axis, wherein said air plenum is oriented perpendicular to said combustion chamber, and wherein said flow passage is oriented perpendicular to said centerline axis.

17 - 19 . (canceled)

20 . A turbine engine assembly comprising:
a plurality of rotating detonation combustors, wherein each rotating detonation combustor comprises: a combustion chamber configured for a rotating detonation process to produce a flow of combustion gas; an air plenum configured to contain a volume of air; a flow passage coupled in flow communication between said combustion chamber and said air plenum and configured to channel an airflow from said air plenum, wherein said flow passage comprises a plurality of fuel mixing mechanisms; a fuel inlet coupled in flow communication with said flow passage and configured to channel a fuel flow into said flow passage, wherein said plurality of fuel mixing mechanisms are configured to mix said airflow and said fuel flow within said combustion chamber; and a turbine coupled downstream from said plurality of rotating detonation combustors, said turbine configured to receive the flow of combustion gas, wherein said combustion chamber comprises an end wall that at least partially defines said flow passage.

Assignees

• Gen Electric

Inventors

• Rickey Owen James Sullivan
• Tangirala Venkat Eswarlu
• Joshi Narendra Digamber
• Yellapantula Shashank

Classifications

• F02C7/22 Primary

  Fuel supply systems · CPC title

• F23R7/00 Primary

  Intermittent or explosive combustion chambers · CPC title

• F02C5/04

  the combustion chambers being formed at least partly in the turbine rotor · CPC title

• F05D2220/62

  with energy recovery turbines · CPC title

• F23R3/425

  Combustion chambers comprising a tangential or helicoidal arrangement of the flame tubes · CPC title