US20180180289A1

US20180180289A1 - Turbine engine assembly including a rotating detonation combustor

Info

Publication number: US20180180289A1
Application number: US15/390,052
Authority: US
Inventors: Thomas Michael Lavertu, Jr.; Andrew Maxwell Peter; Venkat Eswarlu Tangirala; James Albert Tallman; Anthony John Dean
Original assignee: General Electric Co
Current assignee: General Electric Co
Priority date: 2016-12-23
Filing date: 2016-12-23
Publication date: 2018-06-28

Abstract

A turbine engine assembly including a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly also includes a first compressor configured to discharge a flow of cooling air towards the rotating detonation combustor, and to channel the flow of cooling air through the cooling conduit.

Description

BACKGROUND

The present disclosure relates generally to rotating detonation combustion systems and, more specifically, to systems and methods of cooling a rotating detonation combustor.
In rotating detonation engines and, more specifically, in rotating detonation combustors, a mixture of fuel and an oxidizer is ignited such that combustion products are formed. For example, the combustion process begins when the fuel-oxidizer mixture in a tube or a pipe structure is ignited via a spark or another suitable ignition source to generate a compression wave. The compression wave is followed by a chemical reaction that transitions the compression wave to a detonation wave. The detonation wave enters a combustion chamber of the rotating detonation combustor and travels along the combustion chamber. Air and fuel are separately fed into the rotating detonation combustion chamber and are consumed by the detonation wave. As the detonation wave consumes air and fuel, combustion products traveling along the combustion chamber accelerate and are discharged from the combustion chamber. However, rotating detonation combustors generally operate at high local combustion temperatures greater than the temperature limit of materials used to form at least some portions of the rotating detonation combustor.

BRIEF DESCRIPTION

In one aspect, a turbine engine assembly is provided. The assembly includes a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly also includes a first compressor configured to discharge a flow of cooling air towards the rotating detonation combustor, and to channel the flow of cooling air through the cooling conduit.
In another aspect, a rotating detonation combustor is provided. The combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit configured to channel cooling air therethrough. The cooling conduit extends along at least one of the radially inner side wall or the radially outer side wall.
In yet another aspect, a turbine engine assembly is provided. The assembly includes a rotating detonation combustor configured to combust a fuel-air mixture. The rotating detonation combustor includes a radially inner side wall, a radially outer side wall extending about the radially inner side wall such that an annular combustion chamber is at least partially defined therebetween, and a cooling conduit extending along at least one of the radially inner side wall or the radially outer side wall. The assembly further includes a source of cooling fluid coupled in flow communication with the rotating detonation combustor. The source of cooling fluid is configured to discharge a flow of cooling fluid towards the rotating detonation combustor, and to channel the flow of cooling fluid through the cooling conduit. The cooling fluid includes at least one of steam, water, or fuel.

DRAWINGS

These and other features, aspects, and advantages of the present disclosure will become better understood when the following detailed description is read with reference to the accompanying drawings in which like characters represent like parts throughout the drawings, wherein:

FIG. 1 is a schematic illustration of an exemplary combined cycle power generation system;

FIG. 2 is a schematic illustration of an exemplary rotating detonation combustor that may be used in the gas turbine engine assembly shown in FIG. 1;

FIG. 3 is a schematic illustration of the rotating detonation combustor shown in FIG. 2, in accordance with a second embodiment of the disclosure;

FIG. 4 is an enlarged cross-sectional view of a portion of the rotating detonation combustor shown in FIG. 2, taken along Area 4;

FIG. 5 is an enlarged cross-sectional view of a portion of the rotating detonation combustor shown in FIG. 2, taken along Area 5;

FIG. 6 is a schematic illustration of an exemplary rotating detonation combustion system that may be used in the combined cycle power generation system shown in FIG. 1;

FIG. 7 is a schematic illustration of an alternative rotating detonation combustion system that may be used in the combined cycle power generation system shown in FIG. 1;

FIG. 8 is an enlarged cross-sectional view of a portion of the rotating detonation combustor shown in FIG. 7, taken along Area 8; and

FIG. 9 is a further alternative rotating detonation combustion system that may be used in the combined cycle power generation system shown in FIG. 1.

Unless otherwise indicated, the drawings provided herein are meant to illustrate features of embodiments of the disclosure. These features are believed to be applicable in a wide variety of systems comprising one or more embodiments of the disclosure. As such, the drawings are not meant to include all conventional features known by those of ordinary skill in the art to be required for the practice of the embodiments disclosed herein.

DETAILED DESCRIPTION

In the following specification and the claims, reference will be made to a number of terms, which shall be defined to have the following meanings.
The singular forms “a”, “an”, and “the” include plural references unless the context clearly dictates otherwise.
“Optional” or “optionally” means that the subsequently described event or circumstance may or may not occur, and that the description includes instances where the event occurs and instances where it does not.
Approximating language, as used herein throughout the specification and claims, may be applied to modify any quantitative representation that could permissibly vary without resulting in a change in the basic function to which it is related. Accordingly, a value modified by a term or terms, such as “about”, “approximately”, and “substantially”, are not to be limited to the precise value specified. In at least some instances, the approximating language may correspond to the precision of an instrument for measuring the value. Here and throughout the specification and claims, range limitations may be combined and/or interchanged. Such ranges are identified and include all the sub-ranges contained therein unless context or language indicates otherwise.
Embodiments of the present disclosure relate to systems and methods of cooling a rotating detonation combustor. More specifically, the systems described herein include a rotating detonation combustor including an annular combustion chamber defined by a radially inner side wall and a radially outer side wall, and at least one cooling conduit positioned for cooling one or both of the radially inner side wall or the radially outer side wall. The cooling conduit described herein cools the side walls by channeling a cooling fluid therethrough, such as cooling air (i.e., an oxidizer), fuel, steam, or water. As such, the rotating detonation combustor described herein is capable of producing detonations while still operating within predefined material temperature limits.
As used herein, “detonation” and “quasi-detonation” may be used interchangeably. Typical embodiments of detonation chambers include a means of igniting a fuel/oxidizer mixture, for example a fuel/air mixture, and a confining chamber, in which pressure wave fronts initiated by the ignition process coalesce to produce a detonation wave. Each detonation or quasi-detonation is initiated either by external ignition, such as spark discharge or laser pulse, or by gas dynamic processes, such as shock focusing, autoignition or by another detonation via cross-firing. The geometry of the detonation chamber is such that the pressure rise of the detonation wave expels combustion products out the detonation chamber exhaust to produce a thrust force. In addition, rotating detonation combustors are designed such that a substantially continuous detonation wave is produced and discharged therefrom. As known to those skilled in the art, detonation may be accomplished in a number of types of detonation chambers, including detonation tubes, shock tubes, resonating detonation cavities, and annular detonation chambers.
FIG. 1 is a schematic illustration of an exemplary combined cycle power generation system 100. Power generation system 100 includes a gas turbine engine assembly 102 and a steam turbine engine assembly 104. Gas turbine engine assembly 102 includes a compressor 106, a combustor 108, and a first turbine 110 powered by expanding hot gas produced in combustor 108 for driving an electrical generator 112. Gas turbine engine assembly 102 may be used in a stand-alone simple cycle configuration for power generation or mechanical drive applications. In the exemplary embodiment, exhaust gas 114 is channeled from first turbine 110 towards a heat recovery steam generator (HRSG) 116 for recovering waste heat from exhaust gas 114. More specifically, HRSG 116 transfers heat from exhaust gas 114 to water/steam 118 channeled through HRSG 116 to produce steam 120. Steam turbine engine assembly 104 includes a second turbine 122 that receives steam 120, which powers second turbine 122 for further driving electrical generator 112.
In operation, air enters gas turbine engine assembly 102 through an intake 121 and is channeled through multiple stages of compressor 106 towards combustor 108. Compressor 106 compresses the air and the highly compressed air is channeled from compressor 106 towards combustor 108 and mixed with fuel. The fuel-air mixture is combusted within combustor 108. High temperature combustion gas generated by combustor 108 is channeled towards first turbine 110. Exhaust gas 114 is subsequently discharged from first turbine 110 through an exhaust 123.
FIG. 2 is a schematic illustration of an exemplary rotating detonation combustor 124 that may be used in gas turbine engine assembly 102 (shown in FIG. 1). In the exemplary embodiment, rotating detonation combustor 124 (i.e., combustor 108 (shown in FIG. 1)) includes a radially outer side wall 126 and a radially inner side wall 128 that both extend circumferentially relative to a centerline 130 of rotating detonation combustor 124. As such, an annular combustion chamber 132 is defined between radially outer side wall 126 and radially inner side wall 128. In addition, rotating detonation combustor 124 includes a fuel-air mixer 134 coupled within annular combustion chamber 132. Fuel-air mixer 134 receives fuel 136 and air (not shown), and rotating detonation combustor 124 combusts a fuel-air mixture 138 discharged from fuel-air mixer 134. Moreover, rotating detonation combustor 124 channels fuel-air mixture 138 in a first direction 140 within annular combustion chamber 132. While shown as traveling in an axial direction along the length of rotating detonation combustor 124, it should be understood that fuel-air mixture 138 also flows helically within annular combustion chamber 132.
In further embodiments, annular combustion chamber 132 is any suitable geometric shape and does not necessarily include an inner liner and/or center body. For example, in some embodiments, annular combustion chamber 132 is substantially cylindrical.
Rotating detonation combustor 124 further includes a cooling conduit 142 extending along at least one of radially outer side wall 126 or radially inner side wall 128. For example, rotating detonation combustor 124 includes at least one annular jacket radially spaced from at least one of radially outer side wall 126 or radially inner side wall 128 for at least partially defining cooling conduit 142. More specifically, in one embodiment, a first annular jacket 144 is spaced from radially outer side wall 126 such that a first cooling conduit 146 is defined between radially outer side wall 126 and first annular jacket 144. In addition, a second annular jacket 148 is spaced from radially inner side wall 128 such that a second cooling conduit 150 is defined between radially inner side wall 128 and second annular jacket 148. In an alternative embodiment, and as applicable to the other embodiments described herein, cooling is provided to either radially outer side wall 126 or radially inner side wall 128, but not both, with a single cooling conduit.
In the exemplary embodiment, compressor 106 (shown in FIG. 1) discharges a flow of cooling air 152 towards rotating detonation combustor 124 such that the flow of cooling air 152 is channeled through cooling conduits 142. As such, heat produced by the combustion of fuel-air mixture 138 is conducted through radially outer side wall 126 and radially inner side wall 128, and transferred to cooling air 152 channeled through cooling conduits 142. In one embodiment, compressor 106 is coupled in flow communication with rotating detonation combustor 124 such that the flow of cooling air 152 is channeled within first cooling conduit 146 and second cooling conduit 150 in a second direction 154 opposite from first direction 140. In addition, first cooling conduit 146 and second cooling conduit 150 are oriented such that the flow of cooling air 152 channeled therethrough is further channeled towards fuel-air mixer 134 such that fuel-air mixture 138 is formed from cooling air 152. In other words, first cooling conduit 146 and second cooling conduit 150 are oriented such that the flow of cooling air 152 is channeled in a direction that enables cooling air 152 to be combined with fuel 136 and included in fuel-air mixture 138. More specifically, cooling air 152 enters rotating detonation combustor 124 at a first end 153 thereof, and flows in second direction 154 towards towards a second end 155 of rotating detonation combustor 124. Cooling air 152 is then injected into annular combustion chamber 132 for mixing with fuel 136.
Moreover, in one embodiment, cooling conduits 142 and fuel-air mixer 134 are coupled in flow communication such that the air in fuel-air mixture 138 is derived entirely from the flow of cooling air 152, and such that no air from compressor 106 bypasses annular combustion chamber 132. As such, limiting airflow bypass facilitates enhancing the pressure gain capability of rotating detonation combustor 124 such that the efficiency of gas turbine engine 102 is increased.
Rotating detonation combustor 124 further includes a first end plate 156 and a second end plate 158. First end plate 156 is coupled to radially outer side wall 126 and radially inner side wall 128 such that annular combustion chamber 132 is at least partially defined by first end plate 156. First end plate 156 includes an air inlet 160 defined therein. Air inlet 160 is positioned to couple cooling conduits 142 in flow communication with annular combustion chamber 132 upstream of fuel-air mixer 134. Second end plate 158 is spaced from first end plate 156 such that cooling conduits 142 are at least partially defined therefrom. As such, cooling air 152 channeled through first cooling conduit 146 and second cooling conduit 150 is channeled towards air inlet 160 for injection into annular combustion chamber 132 and for mixing with fuel 136 to form fuel-air mixture 138.
FIG. 3 is a schematic illustration of rotating detonation combustor 124 in accordance with a second embodiment of the disclosure. As described above, rotating detonation combustor 124 channels fuel-air mixture 138 in first direction 140 within annular combustion chamber 132. In the exemplary embodiment, second cooling conduit 150 extends along radially inner side wall 128, and compressor 106 (shown in FIG. 1) is coupled in flow communication with rotating detonation combustor 124 such that the flow of cooling air 152 within second cooling conduit 150 is likewise channeled in first direction 140 for discharge towards first turbine 110 (shown in FIG. 1). In such an embodiment, the air in fuel-air mixture 138 is derived entirely from the flow of cooling air 152 channeled through first cooling conduit 146. As such, channeling cooling air 152 in first direction 140 provides cooling along radially inner side wall 128 and provides purging and pilot flame holding capabilities for rotating detonation combustor 124.
FIG. 4 is an enlarged cross-sectional view of a portion of rotating detonation combustor 124, taken along Area 4 (shown in FIG. 2). In the exemplary embodiment, rotating detonation combustor 124 further includes a plurality of thermally conductive projection members 162 extending into an interior 164 of first cooling conduit 146. Thermally conductive projection member 162 provides a heat sink for heat produced by combustion of fuel-air mixture 138 (shown in FIG. 2) and conducted through radially outer side wall 126. As such, heat dissipation from radially outer side wall 126 is improved. As shown, thermally conductive projection members 162 extend into interior 164 of first cooling conduit 146 from radially outer side wall 126. Alternatively, or in addition to thermally conductive projection members 162 extending from radially outer side wall 126, thermally conductive projection members 162 extend into second cooling conduit 150 from radially inner side wall 128 (both shown in FIG. 2). In addition, thermally conductive projection member 162 acts as a turbulator to facilitate vitiating the flow of cooling air 152 channeled across radially outer side wall 126, thereby increasing heat transfer to cooling air 152.
FIG. 5 is an enlarged cross-sectional view of a portion of rotating detonation combustor 124, taken along Area 5 (shown in FIG. 2). In the exemplary embodiment, cooling conduit 142 extends within a thickness portion of at least one of radially outer side wall 126 or radially inner side wall 128. As shown, cooling conduit 142 extends within the thickness portion of radially outer side wall 126. In addition, at least a portion of radially outer side wall 126 is recessed relative to an interior 166 of annular combustion chamber 132 such that one or more stepped side wall portions 168 are formed. Each stepped side wall portion 168 defines an air pocket 170 within annular combustion chamber 132, and includes an opening 172 defined therein that couples cooling conduit 142 in flow communication with air pocket 170. As such, at least a portion of cooling air 152 channeled within cooling conduit 142 flows into air pocket 170, thereby forming an air isolation layer 174 within annular combustion chamber 132. As such, air isolation layer 174 provides cooling and pressure force dampening, induced by detonative combustion, for radially outer side wall 126.
FIG. 6 is a schematic illustration of an exemplary rotating detonation combustion (RDC) system 176 that may be used in combined cycle power generation system 100 (shown in FIG. 1). In the exemplary embodiment, RDC system 176 includes rotating detonation combustor 124 and a source 178 of cooling fluid, such as steam or water 180. Source 178 of cooling fluid channels cooling fluid, such as steam or water 180, towards rotating detonation combustor 124, and channels the flow of cooling fluid through cooling conduits 142. As such, heat produced by the combustion of fuel-air mixture 138 is transferred to steam or water 180 such that heated steam or water 182 is formed. Rotating detonation combustor 124 then channels a flow of heated steam or water 182 from cooling conduits 142 towards second turbine 122 (shown in FIG. 1) for use in the bottoming cycle thereof to facilitate power generation. As such, cooling is provided to rotating detonation combustor 124 and heat produced by the combustion of fuel-air mixture 138 is utilized in an effective and thermally efficient manner.
FIG. 7 is a schematic illustration of an alternative RDC system 184 that may be used in combined cycle power generation system 100 (shown in FIG. 1), and FIG. 8 is an enlarged cross-sectional view of a portion of rotating detonation combustor 124, taken along Area 8 (shown in FIG. 7). In the exemplary embodiment, RDC system 184 includes rotating detonation combustor 124 and a source 186 of cooling fluid, such as fuel 136. In operation, source 186 of cooling fluid channels fuel 136 through cooling conduits 142.
In addition, referring to FIG. 8, radially outer side wall 126 includes at least one fuel inlet 188 defined therein. Specifically, a plurality of fuel inlets 188 are spaced axially from each other relative to centerline 130 (shown in FIG. 2) of rotating detonation combustor 124. Fuel inlets 188 inject fuel 136, in the form of fuel jets 190, into annular combustion chamber 132 for mixing with fuel-air mixture 138. Moreover, rotating detonation combustor 124 includes fuel-air mixer 134, and fuel-air mixer 134 is positioned within annular combustion chamber 132 upstream from the plurality of fuel inlets 188 relative to a flow direction of fuel-air mixture 138. As such, staged fuel injection longitudinally relative to centerline 130 (shown in FIG. 2) facilitates improving mixing of the fuel and air, and facilitates controlling the equivalence ratio of the fuel-air mixture along the axial length of rotating detonation combustor 124. Moreover, staged fuel injection also facilitates improving the fill length of rotating detonation combustor 124.
FIG. 9 is a further alternative RDC system 192 that may be used in combined cycle power generation system 100 (shown in FIG. 1). In the exemplary embodiment, RDC system 192 includes a second compressor 194 coupled downstream from and that receives a flow of bleed air 196 from compressor 106. Second compressor 194 compresses the flow of bleed air 196, and discharges a flow of boosted cooling air 198 towards rotating detonation combustor 124 such that fuel-air mixture 138 (shown in FIG. 2) is formed from a mixed flow of cooling air 152 (shown in FIG. 2) and boosted cooling air 198. As such, using boosted cooling air 198 to cool rotating detonation combustor 124 facilitates improving the cooling effectiveness provided to rotating detonation combustor 124 from the cooling fluid.
In some embodiments, RDC system 192 includes a cooling device 200 positioned between compressor 106 and second compressor 194. Cooling device 200 cools the flow of bleed air 196 before being channeled towards second compressor 194. As such, compression of bleed air 196 within second compressor 194 is provided in a more cost effective manner relative to compressing uncooled air.
The systems and methods described herein facilitate providing cooling to a rotating detonation combustor. The cooling is provided by channeling a cooling fluid through one or more cooling conduits that extend along a radially outer side wall or a radially inner side wall of the rotating detonation combustor. In addition, the system described herein facilitates using the heat generated by combustion to improve the thermal efficiency of related assemblies.
An exemplary technical effect of the systems and methods described herein includes at least one of: (a) providing cooling to a rotating detonation combustor; (b) increasing the efficiency of a gas turbine engine; and (c) utilizing one or more architectural cooling concepts to improve the thermal efficiency of a turbine engine assembly.
Exemplary embodiments of RDC systems are provided herein. The systems and methods are not limited to the specific embodiments described herein, but rather, components of systems and/or steps of the methods may be utilized independently and separately from other components and/or steps described herein. For example, the configuration of components described herein may also be used in combination with other processes, and is not limited to practice with only ground-based, combined cycle power generation systems, as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many applications where a RDC system may be implemented.
Although specific features of various embodiments of the present disclosure may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of embodiments of the present disclosure, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing.
This written description uses examples to disclose the embodiments of the present disclosure, including the best mode, and also to enable any person skilled in the art to practice embodiments of the present disclosure, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the embodiments described herein is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.

Claims

What is claimed is:

1. A turbine engine assembly comprising:

a rotating detonation combustor configured to combust a fuel-air mixture, wherein said rotating detonation combustor comprises:

a radially inner side wall;

a radially outer side wall extending about said radially inner side wall such that an annular combustion chamber is at least partially defined therebetween; and

a cooling conduit extending along at least one of said radially inner side wall or said radially outer side wall; and

a first compressor configured to discharge a flow of cooling air towards said rotating detonation combustor and configured to channel the flow of cooling air through said cooling conduit.

2. The turbine engine assembly in accordance with claim 1, wherein said rotating detonation combustor further comprises an annular jacket radially spaced from at least one of said radially inner side wall or said radially outer side wall, said annular jacket at least partially defining said cooling conduit.

3. The turbine engine assembly in accordance with claim 1, wherein said rotating detonation combustor is configured to channel the fuel-air mixture in a first direction within said annular combustion chamber, said first compressor coupled in flow communication with said rotating detonation combustor such that the flow of cooling air is channeled in a second direction, opposite from the first direction, within said cooling conduit.

4. The turbine engine assembly in accordance with claim 1, wherein said cooling conduit extends along said radially inner side wall, wherein said rotating detonation combustor is configured to channel the fuel-air mixture in a first direction within said annular combustion chamber, and wherein said first compressor is coupled in flow communication with said rotating detonation combustor such that the flow of cooling air is channeled in the first direction within said cooling conduit.

5. The turbine engine assembly in accordance with claim 1, wherein said rotating detonation combustor further comprises a fuel-air mixer configured to receive fuel and air to form the fuel-air mixture, said cooling conduit oriented such that the flow of cooling air channeled therethrough is further channeled towards said fuel-air mixer such that the fuel-air mixture is formed from the cooling air.

6. The turbine engine assembly in accordance with claim 5, wherein said cooling conduit and said fuel-air mixer are coupled in flow communication such that the air in the fuel-air mixture is derived entirely from the flow of cooling air.

7. The turbine engine assembly in accordance with claim 1 further comprising a second compressor configured to receive a flow of bleed air from said first compressor, and configured to discharge a flow of boosted cooling air towards said rotating detonation combustor such that the fuel-air mixture is formed from a mixed flow of cooling air and boosted cooling air.

8. The turbine engine assembly in accordance with claim 7 further comprising a cooling device positioned between said first compressor and said second compressor, said cooling device configured to cool the flow of bleed air before being channeled towards said second compressor.

9. A rotating detonation combustor comprising:

a radially inner side wall;

a cooling conduit configured to channel cooling air therethrough, said cooling conduit extending along at least one of said radially inner side wall or said radially outer side wall.

10. The rotating detonation combustor in accordance with claim 9 further comprising a plurality of thermally conductive projection members extending into an interior of said cooling conduit from at least one of said radially inner side wall or said radially outer side wall.

11. The rotating detonation combustor in accordance with claim 9 further comprising:

a first end plate coupled to said radially inner side wall and said radially outer side wall, said first end plate at least partially defining said annular combustion chamber, wherein said first end plate comprises an air inlet defined therein; and

a second end plate spaced from said first end plate and at least partially defining said cooling conduit such that the cooling air channeled therethrough is further channeled towards said air inlet.

12. The rotating detonation combustor in accordance with claim 9 further comprising a first annular jacket radially spaced from said radially outer side wall such that said cooling conduit is defined between said radially outer side wall and said first annular jacket.

13. The rotating detonation combustor in accordance with claim 9 further comprising a second annular jacket radially spaced from said radially inner side wall such that said cooling conduit is defined between said radially inner side wall and said second annular jacket.

14. The rotating detonation combustor in accordance with claim 9, wherein said cooling conduit extends within a portion of at least one of said radially inner side wall or said radially outer side wall.

15. The rotating detonation combustor in accordance with claim 14, wherein at least a portion of said at least one of said radially inner side wall or said radially outer side wall is recessed relative to an interior of said annular combustion chamber such that a stepped side wall portion is formed, said stepped side wall portion defining an air pocket within said annular combustion chamber, and said stepped side wall portion comprising an opening defined therein that couples said cooling conduit in flow communication with said air pocket.

16. A turbine engine assembly comprising:

a radially inner side wall;

a source of cooling fluid coupled in flow communication with said rotating detonation combustor, said source of cooling fluid configured to discharge a flow of cooling fluid towards said rotating detonation combustor, and configured to channel the flow of cooling fluid through said cooling conduit, wherein the cooling fluid includes at least one of steam, water, or fuel.

17. The turbine engine assembly in accordance with claim 16, wherein said source of cooling fluid is configured to channel steam or water through said cooling conduit such that heated steam or heated water is formed, said turbine engine assembly further comprising a steam turbine configured to receive a flow of heated steam or heated water from said cooling conduit.

18. The turbine engine assembly in accordance with claim 16, wherein said source of cooling fluid is configured to channel fuel through said cooling conduit, wherein at least one of said radially inner side wall or said radially outer side wall comprises at least one fuel inlet defined therein, said at least one fuel inlet configured to inject the fuel into said annular combustion chamber.

19. The turbine engine assembly in accordance with claim 18, wherein said at least one fuel inlet comprises a plurality of fuel inlets spaced axially from each other relative to a centerline of said rotating detonation combustor.

20. The turbine engine assembly in accordance with claim 18, wherein said rotating detonation combustor further comprises a fuel-air mixer positioned within said annular combustion chamber upstream from said at least one fuel inlet relative to a flow direction of the fuel-air mixture.