This disclosure relates generally to a turbine engine and, more particularly, to heat transfer within a turbine engine.
A modern gas turbine engine includes various internal components that are subject to relatively high temperatures. To prevent material fatigue and deterioration, it is known in the art to bleed compressed air from a compressor section of the turbine engine and route that bleed air to select internal components for cooling. Bleeding compressed air from the compressor section, however, decreases efficiency of the turbine engine. In addition, as turbine engines are made more and more compact, it may be increasingly more difficult to include internal passages for routing the bleed air from the compressor section to the air cooled components. There is a need in the art therefore for alternative techniques for cooling internal components/structures of a turbine engine.
According to an aspect of the present disclosure, an assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine airfoil and a heat pipe. The heat pipe is configured with the turbine engine airfoil. The heat pipe includes a closed-loop internal fluid circuit.
According to another aspect of the present disclosure, another assembly is provided for a turbine engine. This turbine engine assembly includes a turbine engine case and a heat pipe. The heat pipe includes a working fluid and a closed-loop internal fluid circuit. The closed-loop internal fluid circuit extends within a sidewall of the turbine engine case. The heat pipe is configured to flow the working fluid through the closed-loop internal fluid circuit.
According to still another aspect of the present disclosure, an apparatus is provided for a turbine engine. This turbine engine apparatus includes a heat pipe that extends longitudinally between a first end and a second end. The heat pipe includes a working fluid, a gas passage, a liquid passage and a lattice structure in contact with the working fluid. The heat pipe is configured to flow the working fluid in a gaseous phase through the gas passage. The heat pipe is configured to flow the working fluid in a liquid phase through the liquid passage.
The turbine engine assembly may also include a turbine engine vane. The closed-loop internal fluid circuit may extend within the turbine engine vane.
The turbine engine apparatus may also include a turbine engine component. The gas passage and the liquid passage may extend within the turbine engine component.
The gas passage and the liquid passage may be at least partially formed by and extend through the lattice structure.
The lattice structure may be disposed within the liquid passage.
The turbine engine airfoil may be configured as a vane.
The vane may be configured as or otherwise include a turbine vane or a diffuser vane.
The heat pipe may be formed integral with the turbine engine airfoil.
A passage of the heat pipe may extend within the turbine engine airfoil.
The heat pipe may also include a working fluid. The heat pipe may be configured to circulate the working fluid through the closed-loop internal fluid circuit.
The closed-loop internal fluid circuit may include a first passage and a second passage. The heat pipe may be configured to flow the working fluid in a first phase through the first passage. The heat pipe may be configured to flow the working fluid in a second phase through the second passage. The heat pipe may include a lattice structure that forms the first passage and the second passage.
The closed-loop internal fluid circuit may include a first passage and a second passage. The heat pipe may be configured to flow the working fluid in a first phase through the first passage. The heat pipe may be configured to flow the working fluid in a second phase through the second passage. The heat pipe may include a lattice structure within the second passage.
The closed-loop internal fluid circuit may include a first passage and a second passage. The heat pipe may be configured to flow the working fluid in a first phase through the first passage. The heat pipe may be configured to flow the working fluid in a second phase through the second passage. The heat pipe may include sintered powder within the second passage.
The heat pipe may include a working fluid, a gas passage and a liquid passage. The heat pipe may be configured to: (A) transfer heat energy into the working fluid in a liquid phase at a first end of the heat pipe to at least partially change phase of the working fluid into a gaseous phase; (B) direct the working fluid in the gaseous phase through the gas passage from the first end of the heat pipe to a second end of the heat pipe; (C) transfer the heat energy out of the working fluid in the gaseous phase at the second end of the heat pipe to at least partially change phase the working fluid into the liquid phase; and (D) direct the working fluid in the liquid phase through the liquid passage from the second end of the heat pipe to the first end of the heat pipe.
The turbine engine assembly may also include a turbine engine case. The airfoil may be connected to the turbine engine case. The heat pipe may also be configured with a sidewall of the turbine engine case.
The turbine engine assembly may also include a second turbine engine airfoil connected to the turbine engine case. The heat pipe may be configured with the second turbine engine airfoil.
The turbine engine case may be radially between the turbine engine airfoil and the second turbine engine airfoil. A passage of the heat pipe may extend out of the turbine engine airfoil, through the sidewall of the turbine engine case, and into the second turbine engine airfoil.
The turbine engine assembly may also include thermal insulation surrounding a portion of the heat pipe.
The present disclosure may include any one or more of the individual features disclosed above and/or below alone or in any combination thereof
The foregoing features and the operation of the invention will become more apparent in light of the following description and the accompanying drawings.
The turbine engine structure 22 may be configured as any component, or assembly of components, within the turbine engine. The turbine engine structure 22, for example, may be configured as or otherwise include an aero component disposed within and/or otherwise configured to interact with fluid (e.g., core gas) flowing through a flowpath (e.g., a core flowpath) of the turbine engine. An example of such an aero component is a turbine engine airfoil such as, but not limited to, a fixed or variable turbine engine vane or an airfoil of a turbine engine rotor blade. The turbine engine structure 22 may also or alternatively be configured as or otherwise include a flowpath component configured to form a peripheral boundary of the flowpath of the turbine engine. An example of such a flowpath component is a turbine engine case. The present disclosure, however, is not limited to such exemplary turbine engine structure components. The turbine engine structure 22, for example, may also or alternatively be configured as or otherwise include a support structure component such as, but not limited to, a strut or a frame.
The heat source 24 may be configured as any component, assembly of components and/or fluid(s) within the turbine engine that generates heat energy, conveys heat energy and/or is otherwise subject to relatively high quantities of heat energy. The heat source 24, for example, may be a combustor of the turbine engine and/or combustion products (e.g., hot core gas) directed from the combustor into and through a turbine section of the turbine engine. Of course, various other heat sources (e.g., bodies and/or fluids) capable of generating heat energy, conveying heat energy and/or that are otherwise subject to relatively high quantities of heat energy are present in a turbine engine, and the present disclosure is not limited to any particular ones thereof
The heat sink 26 may be configured as any component, assembly of components and/or fluid(s) within the turbine engine capable of absorbing heat energy. The heat sink 26, for example, may be a diffuser duct of the turbine engine and/or fluid (e.g., relatively cool core gas) directed through the diffuser duct into a diffuser plenum surrounding the combustor. Of course, various other heat sinks (e.g., bodies and/or fluids) capable of absorbing heat energy are present in a turbine engine, and the present disclosure is not limited to any particular ones thereof.
The heat transfer device 28 is configured to (e.g., passively) transfer heat energy between the heat source 24 and the heat sink 26. More particularly, the heat transfer device 28 is configured to receive (e.g., absorb) heat energy from the heat source 24 and then transfer (e.g., reject) that received heat energy into the heat sink 26. The heat transfer device 28 may thereby cool the heat source 24 and heat the heat sink 26.
The heat transfer device 28 of
The heat pipe 30 includes a closed-loop internal fluid circuit 38 for circulating a working fluid (e.g., a phase change material) within the heat pipe 30 between the heat pipe first end 34 and the heat pipe second end 36. The fluid circuit 38 of
The working fluid is configured as is a multi-phase (e.g., two-phase) working fluid. The working fluid, for example, is operable to change phase between a gaseous phase and a liquid phase during heat pipe operation. An example of the working fluid is a fluid including sodium (Na) and/or potassium (K). Another example of the working fluid is refrigerant. The present disclosure, however, is not limited to the foregoing exemplary working fluids.
During turbine engine operation, the heat pipe 30 transfers heat energy from the heat source 24 into the working fluid at the heat pipe first end 34. More particularly, the heat pipe 30 transfers the heat energy into a quantity of the working fluid within a first phase change region 42 (e.g., an evaporator and/or a vaporizer) of the heat pipe 30 at the heat pipe first end 34. During this heat energy transfer, the working fluid within the first phase change region 42 absorbs at least some or all of the heat energy received from the heat source 24. This heat energy absorption heats the working fluid such that a liquid phase of the working fluid (“liquid working fluid”) may change phase to a gaseous phase of the working fluid (“gaseous working fluid”). The liquid working fluid may thereby evaporate or vaporize into the gaseous working fluid. This gaseous working fluid is subsequently directed (e.g., flows) through the gas passage 40A from the heat pipe first end 34 to the heat pipe second end 36.
At the heat pipe second end 36, the heat pipe 30 transfers heat energy (e.g., some or all of the heat energy previous absorbed from the heat source 24) from the working fluid into the heat sink 26. More particularly, the heat pipe 30 transfers the heat energy out of a quantity of the working fluid within a second phase change region 44 (e.g., a condenser) of the heat pipe 30 at the heat pipe second end 36. During this heat energy transfer, the working fluid within the second phase change region 44 rejects at least some or all of the heat energy into the heat sink 26. This heat energy rejection cools the working fluid such that the gaseous phase of the working fluid may change phase to the liquid phase of the working fluid. The gaseous working fluid may thereby condense into the liquid working fluid. This liquid working fluid is subsequently directed (e.g., flows) through the liquid passage 40B from the heat pipe second end 36 back to the heat pipe first end 34 in order to, for example, repeat the heat transfer cycle.
To promote the flow of the gaseous phase of the working fluid through the gas passage 40A from the heat pipe first end 34 to the heat pipe second end 36, the gas passage 40A may be configured substantially unobstructed. An internal channel 46A (e.g., bore) of the gas passage 40A, for example, may be hollow; e.g., empty except for the working fluid therein. In addition or alternatively, the heat pipe 30 may be arranged such that the heat pipe second end 36 is vertically above (with respect to gravity) the heat pipe first end 34. The heat transfer device 28 and its heat pipe 30, of course, may also or alternatively utilize one or more other devices and/or fluid principles to promote the flow of the gaseous working fluid through the gas passage 40A and its channel 46A.
To promote the flow of the liquid phase of the working fluid through the liquid passage 40B from the heat pipe second end 36 to the heat pipe first end 34, the liquid passage 40B may be configured with a wicking structure 48. An internal channel 46B (e.g., bore) of the liquid passage 40B, for example, may be at least partially or completely filled with material (the wicking structure 48) having a network of interconnected interstices 50; e.g., pores, cavities, voids, gaps, spaced, micro channels, etc. The interstices 50 may be sized to promote a capillary action (e.g., wicking) of the liquid working fluid. The liquid passage channel 46B, for example, may be at least partially or completely filled with: a lattice structure 52 (see
As turbine engine design trends continue to push bounds of performance and efficiency as well as turbine engine applications, turbine engines may be made more-and-more compact and lightweight. To accommodate these design trends, the heat transfer device 28 of
Referring to
Each of the turbine engine cases 60, 62, 64 extends circumferentially about (e.g., completely around) an axial centerline 70 of the turbine engine 72. Each of the turbine engine cases 60, 62, 64 may thereby be configured as a tubular wall within the turbine engine 72.
The inner case 60 is disposed radially within the intermediate case 62 such that the intermediate case 62 circumscribes and axially overlaps the inner case 60. The turbine engine cases 60 and 62 are radially spaced from one another so as to form an inner (e.g., annular) duct 74 therebetween. This inner duct 74 may be configured as a turbine inlet duct. The inner duct 74 may thereby form a (e.g., downstream) portion of the core flowpath 76 within the turbine engine 72; e.g., see
The intermediate case 62 is disposed radially within the outer case 64 such that the outer case 64 circumscribes and axially overlaps the intermediate case 62. The turbine engine cases 62 and 64 are radially spaced from one another so as to form an outer (e.g., annular) duct 78 therebetween. This outer duct 78 may be configured as a diffuser inlet duct. The outer duct 78 may thereby form a (e.g., upstream) portion of the core flowpath 76 within the turbine engine 72; e.g., see
The inner nozzle 66 is arranged within the inner duct 74. The inner nozzle 66, for example, is arranged radially between the inner case 60 and the intermediate case 62. The inner nozzle 66 includes a plurality of inner nozzle vanes 80 (e.g., turbine vanes) arranged circumferentially about the axial centerline 70 in an annular array. Each of these inner nozzle vanes 80 has an inner nozzle airfoil 82 that extends radially between and is connected to the inner case 60 and the intermediate case 62. The inner nozzle airfoils 82 may be configured to condition (e.g., turn) gas (e.g., the core gas) flowing through the inner nozzle 66. In addition or alternatively, the inner nozzle vanes 80 and their airfoils 82 may be configured to structurally connect the turbine engine cases 60 and 62 together.
The inner nozzle 66 may be configured as a turbine nozzle. The inner nozzle 66, for example, may be configured as a nozzle arranged at an outlet of a combustion chamber and an inlet to a turbine section; e.g., see
The outer nozzle 68 is arranged within the outer duct 78. The outer nozzle 68, for example, is arranged radially between the intermediate case 62 and the outer case 64. The outer nozzle 68 includes a plurality of outer nozzle vanes 84 (e.g., diffuser vanes) arranged circumferentially about the axial centerline 70 in an annular array. Each of these outer nozzle vanes 84 has an outer nozzle airfoil 86 that extends radially between and is connected to the intermediate case 62 and the outer case 64. The outer nozzle airfoils 86 may be configured to condition (e.g., turn) gas (e.g., the core gas) flowing through the outer nozzle 68. In addition or alternatively, the outer nozzle vanes 84 and their airfoils 86 may be configured to structurally connect the turbine engine cases 62 and 64 together.
The outer nozzle 68 may be configured as a diffuser nozzle. The outer nozzle 68, for example, may be configured as a nozzle arranged at an outlet of a compressor section and an inlet to the diffuser plenum; e.g., see
Referring to
The first phase change region 42 and respective longitudinal lengths of the fluid circuit passages 40 are formed by and extend within the respective inner nozzle vane 80 and its airfoil 82. The heat pipe first end 34, for example, is located at a connection/interface between the respective inner nozzle vane 80 and the inner case 60. The fluid circuit passages 40 extend within an interior of the respective inner nozzle vane 80 along a span of the inner nozzle vane 80 to the intermediate case 62. The fluid circuit passage channels 46 may thereby be respectively formed by internal bores within the respective inner nozzle vane 80, and walls of the fluid circuit passages 40 may thereby be formed by material/walls of the respective inner nozzle vane 80.
An intermediate portion of the fluid circuit 38 and respective longitudinal lengths of the fluid circuit passages 40 are formed by and extend within the intermediate case 62. The fluid circuit passages 40, for example, extend axially within an interior of a sidewall 88 of the intermediate case 62 from a connection/interface between the respective inner nozzle vane 80 and the intermediate case 62 to a connection/interface between the intermediate case 62 and the respective outer nozzle vane 84. The fluid circuit passage channels 46 may thereby be respectively formed by internal bores within the intermediate case sidewall 88, and walls of the fluid circuit passages 40 may thereby be formed by material/walls of the intermediate case 62.
The second phase change region 44 and respective longitudinal lengths of the fluid circuit passages 40 are formed by and extend within the respective outer nozzle vane 84 and its airfoil 86. The heat pipe second end 36, for example, is located at a connection/interface between the respective outer nozzle vane 84 and the outer case 64. The fluid circuit passages 40 extend within an interior of the respective outer nozzle vane 84 along a span of the outer nozzle vane 84 to the intermediate case 62. The fluid circuit passage channels 46 may thereby be respectively formed by internal bores within the respective outer nozzle vane 84, and walls of the fluid circuit passages 40 may thereby be formed by material/walls of the respective outer nozzle vane 84.
With the foregoing arrangement, each heat pipe 30 is configured to absorb heat energy from the respective inner nozzle vane 80 (e.g., turbine vane) and thereby cool that inner nozzle vane 80. This transfer of heat energy may aid in protecting the respective inner nozzle vane 80 from relatively high temperature gas (e.g., combustion products) flowing through the inner nozzle 66. Cooling for the inner nozzle vanes 80 may also be tailored to account for hot streaks in the gas flowing through the inner nozzle 66. Each heat pipe 30 is also configured to reject the absorbed heat energy into the respective outer nozzle vane 84 (e.g., diffuser vane) and thereby heat that outer nozzle vane 84. This transfer of heat energy may aid in pre-heating relatively low temperature gas (e.g., compressed air) flowing through the outer nozzle 68, which can increase turbine engine efficiency.
The heat pipe 30 may be provided with an access port 90 (e.g., a fill port) at the heat pipe second end 36. This access port 90 may be configured to facilitate one or more operations. Examples of these operations may include, but are not limited to:
In some embodiments, referring to
In some embodiments, referring to
In some embodiments, referring to
In some embodiments, referring to
The heat pipe 30 and the turbine engine structure 22 may be integrated together using various different manufacturing and design techniques. For example, the heat pipe 30 and the turbine engine structure 22 may be formed as a (e.g., metal) monolithic body. The term monolithic may describe herein an apparatus which is formed as a single unitary body. The heat pipe 30 and the turbine engine structure 22, for example, may be additively manufactured, cast, machined and/or otherwise formed as an integral, unitary body. Alternatively, the turbine engine assembly 20 and any one or more of its elements may be formed as a non-monolithic body. The term non-monolithic may described an apparatus which includes a plurality of discretely formed parts, where those parts are mechanically fastened and/or otherwise attached to one another to form the apparatus.
The term additive manufacturing may describe a process where a component or components are formed by accumulating and/or fusing material together using an additive manufacturing device, typically in a layer-on-layer manner. Layers of powder material, for example, may be disposed and thereafter solidified sequentially onto one another to form the component(s). The term solidify may describe a process whereby material is sintered and/or otherwise melted thereby causing discrete particles or droplets of the sintered and/or melted material to fuse together. Examples of the additive manufacturing process include a laser powder bed fusion (LPBF) process and an electron beam powder bed fusion (EB-PBF) process. Examples of the additive manufacturing device include a laser powder bed fusion (LPBF) device and an electron beam powder bed fusion (EB-PBF) device. Of course, various other additive manufacturing processes and devices are known in the art, and the present disclosure is not limited to any particular ones thereof
At least a portion of the fluid circuit 38 (e.g., the liquid passage 40B) may be at least partially or completely filled with a wicking structure 48 or other porous material as discussed above; e.g., see
Integrating the heat pipe 30 with the turbine engine structure 22 may facilitate tailored cooling for the turbine engine structure 22. Integrating the heat pipe 30 with the turbine engine structure 22 may facilitate remote cooling of the certain turbine engine components; e.g., cooling without requiring a cooling air source. Integrating the heat pipe 30 with the turbine engine structure 22 may reduce turbine engine space requirements by providing a single component/structure with multiple functions; e.g., an airfoil may (1) condition gas flowing through a flowpath and (2) facilitate heat pipe heat energy transfer. Integrating the heat pipe 30 with the turbine engine structure 22 may also increase a service life of the turbine engine structure 22 or one or more other thermally coupled components, particularly where that turbine engine structure 22 or other component(s) would otherwise not receive cooling; e.g., impingement and/or effusion cooling.
The turbine engine assembly 20 of the present disclosure may be configured with various different types and configurations of turbine engines.
In the specific embodiment of
The turbine engine assembly 20 and any one or more of its components may be included in various turbine engines other than the one described above. The heat pipe 30, for example, may be included in a geared turbine engine where a gear train connects one or more shafts to one or more rotors in a fan section, a compressor section and/or any other engine section. Alternatively, the heat pipe 30 may be included in a turbine engine configured without a gear train. The heat pipe 30 may be included in a geared or non-geared turbine engine configured with a single spool (see
While various embodiments of the present disclosure have been described, it will be apparent to those of ordinary skill in the art that many more embodiments and implementations are possible within the scope of the disclosure. For example, the present disclosure as described herein includes several aspects and embodiments that include particular features. Although these features may be described individually, it is within the scope of the present disclosure that some or all of these features may be combined with any one of the aspects and remain within the scope of the disclosure. Accordingly, the present disclosure is not to be restricted except in light of the attached claims and their equivalents.