Turbine engine assembly including a rotating detonation combustor

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, the air plenum defined by a first wall, a second wall having an air inlet therethrough for providing a flow of air into the air plenum, and a third wall coupling a first end of the first wall and a first end of the second wall;
• a first sidewall extending from the first wall to the combustion chamber and a second sidewall extending from the second wall to the combustion chamber, the first sidewall and the second sidewall defining 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 into the combustion chamber;
• an air flow splitter wall arranged within the air plenum, the air flow splitter wall having a first end extending from the third wall of the air plenum and a second end extending at least partially within said flow passage between said first sidewall and said second sidewall, wherein the air flow splitter wall comprises a plurality of openings positioned within the air plenum upstream of the flow passage, the plurality of openings enabling airflow from the air inlet through the air flow splitter wall to fill the air plenum;
• a plurality of fuel mixing mechanisms coupled to at least one of said air flow splitter wall, said first sidewall, or said second sidewall;
• and
• a plurality of fuel inlets extending through at least one of the first sidewall or the second sidewall and 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.

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, the air plenum defined by a first wall, a second wall having an air inlet therethrough for providing a flow of air into the air plenum, and a third wall coupling a first end of the first wall and a first end of the second wall, the first wall and the second wall converging at a second end of the first wall and a second end of the second wall to define a throat therebetween;
• a flow passage coupled in flow communication between said combustion chamber and an inlet of the throat of said air plenum and configured to channel an airflow from said air plenum into the combustion chamber, wherein said flow passage is defined between a first sidewall extending from the second end of the first wall to the combustion chamber and a second sidewall extending from the second end of the second sidewall to the combustion chamber, and at least one of the first sidewall or the second sidewall includes a plurality of flow passage fuel mixing mechanisms thereon;
• a fuel inlet extending through one of the first sidewall or the second sidewall and coupled in flow communication with said flow passage and configured to channel a fuel flow into said flow passage, wherein said plurality of flow passage fuel mixing mechanisms are configured to mix said airflow and said fuel flow within said combustion chamber;
• and
• a splitter wall arranged within the air plenum, the splitter wall having a first end coupled to the third wall and a second end extending at least partially into said flow passage between the first sidewall and the second sidewall, wherein said splitter wall includes a first side and a second side opposite the first side, and at least one of the first side or the second side includes a plurality of splitter wall fuel mixing mechanisms thereon extending into the flow passage, wherein the splitter wall comprises a plurality of openings positioned within the air plenum upstream of the flow passage, the plurality of openings enabling airflow from the air inlet through the splitter wall to fill the air plenum;
• 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.

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, the air plenum defined by a first wall, a second wall having an air inlet therethrough for providing a flow of air into the air plenum, and a third wall coupling a first end of the first wall and a first end of the second wall;
• a first sidewall extending from the first wall to the combustion chamber and a second sidewall extending from the second wall to the combustion chamber, the first sidewall and the second sidewall defining 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 into the combustion chamber;
• an airflow splitter wall arranged within the air plenum, the airflow splitter wall having a first end extending from the third wall of the air plenum and a second end extending at least partially within said flow passage between the first sidewall and the second sidewall, wherein the airflow splitter wall comprises a plurality of openings positioned within the air plenum upstream of the flow passage, the plurality of openings enabling airflow from the air inlet through the airflow splitter wall to fill the air plenum;
• a plurality of fuel mixing mechanisms coupled to at least one of the airflow splitter wall, said first sidewall, or said second sidewall;
• and
• a plurality of fuel inlets extending through at least one of the first sidewall or the second sidewall and 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.