Turbine engine assembly including a rotating detonation combustor

Patent metadata

Field	Value
Publication number	US-10969107-B2
Application number	US-201715705954-A
Country	US
Kind code	B2
Filing date	Sep 15, 2017
Priority date	Sep 15, 2017
Publication date	Apr 6, 2021
Grant date	Apr 6, 2021

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

What is claimed is:

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, wherein said plurality of fuel mixing mechanisms comprise a plurality of corrugations, wherein said flow passage includes a first sidewall and an opposing second sidewall that define said flow passage therebetween, wherein said first sidewall comprises a first plurality of corrugations, wherein said second sidewall comprises a second plurality of corrugations, wherein said first plurality of corrugations is circumferentially offset with said second plurality of corrugations, and wherein said flow passage defines a uniform width between said first plurality of corrugations and said second plurality of corrugations; and
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 positioned downstream of said fuel inlet and are configured to mix said airflow and said fuel flow within said combustion chamber.

2. The rotating detonation combustor in accordance with claim 1 , further comprising a throat portion defined between said air plenum and said flow passage, wherein said fuel inlet is positioned downstream of said throat portion, and wherein said plurality of fuel mixing mechanisms are positioned downstream from said fuel inlet.

3. The rotating detonation combustor in accordance with claim 1 , wherein said air plenum comprises a pair of converging sidewalls and an end wall coupled between said sidewalls.

4. The rotating detonation combustor in accordance with claim 3 , wherein said end wall is curved between said sidewalls.

5. The rotating detonation combustor in accordance with claim 1 , wherein said first plurality of corrugations comprise a first plurality of peaks and a first plurality of troughs that alternate with said first plurality of troughs, wherein said second plurality of corrugations comprise a second plurality of peaks and a second plurality of troughs that alternate with said second plurality of troughs, and wherein said first plurality of troughs are radially aligned with said second plurality of peaks.

6. The rotating detonation combustor in accordance with claim 1 , further comprising a combustor centerline extending through said air plenum, said flow passage, and said combustion chamber, wherein said air plenum comprises:
a pair of converging sidewalls that are both obliquely oriented with respect to said combustor centerline such that said sidewalls taper towards said flow passage;
an end wall coupled between said sidewalls wherein said end wall is curved between said sidewalls; and
an air inlet positioned between said end wall and said flow passage and oriented perpendicular to said combustor centerline.

7. The rotating detonation combustor in accordance with claim 6 , wherein said plenum is configured to create an opposing pressure wave that stiffens the air within said flow passage to prevent a combustion wave from channeling fluid into said air plenum and configured to push unburnt air back into said combustion chamber.

8. 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, wherein said plurality of fuel mixing mechanisms comprise a plurality of corrugations, wherein said flow passage includes a first sidewall and an opposing second sidewall that define said flow passage therebetween, wherein said first sidewall comprises a first plurality of corrugations, and wherein said second sidewall comprises a second plurality of corrugations, wherein said first plurality of corrugations is circumferentially offset with said second plurality of corrugations, wherein said flow passage defines a uniform width between said first plurality of corrugations and said second plurality of corrugations;
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 positioned downstream of said fuel inlet and 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.

9. The turbine engine assembly in accordance with claim 8 , wherein each rotating detonation combustor further comprises a centerline axis, wherein said air plenum is axially aligned with said combustion chamber, and wherein said flow passage is oriented parallel with said centerline axis.

10. 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, wherein said plurality of fuel mixing mechanisms comprise a plurality of corrugations formed in at least one sidewall of said flow passage;
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 positioned downstream of said fuel inlet and are configured to mix said airflow and said fuel flow within said combustion chamber; and
a combustor centerline extending through said air plenum, said flow passage, and said combustion chamber, wherein said air plenum comprises:
a pair of converging sidewalls that are both obliquely oriented with respect to said combustor centerline such that said sidewalls taper towards said flow passage;
an end wall coupled between said sidewalls wherein said end wall is curved between said sidewalls; and
an air inlet positioned between said end wall and said flow passage and oriented perpendicular to said combustor centerline.

11. The rotating detonation combustor in accordance with claim 10 , wherein said plenum is configured to create an opposing pressure wave that stiffens the air within said flow passage to prevent a combustion wave from channeling fluid into said air plenum and configured to push unburnt air back into said combustion chamber.

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

• F23R3/286

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

• F23R3/425

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

• F02C6/18

  using the waste heat of gas-turbine plants outside the plants themselves, e.g. gas-turbine power heat plants (using waste heat as source of energy for refrigeration plants F25B27/02; using the waste heat of a gasturbine for steam generation or in a steam cycle see F01K23/10) · CPC title

• F02C5/04

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