US20210355879A1 - Systems and methods for cooling an endwall in a rotary machine - Google Patents
Systems and methods for cooling an endwall in a rotary machine Download PDFInfo
- Publication number
- US20210355879A1 US20210355879A1 US16/875,604 US202016875604A US2021355879A1 US 20210355879 A1 US20210355879 A1 US 20210355879A1 US 202016875604 A US202016875604 A US 202016875604A US 2021355879 A1 US2021355879 A1 US 2021355879A1
- Authority
- US
- United States
- Prior art keywords
- pass
- cooling fluid
- flow
- core
- inlet portion
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 238000001816 cooling Methods 0.000 title claims abstract description 46
- 238000000034 method Methods 0.000 title claims description 28
- 239000012809 cooling fluid Substances 0.000 claims abstract description 171
- 230000005465 channeling Effects 0.000 claims description 33
- 238000011144 upstream manufacturing Methods 0.000 claims description 13
- 230000001681 protective effect Effects 0.000 claims description 7
- 238000004891 communication Methods 0.000 claims description 6
- 238000002485 combustion reaction Methods 0.000 claims description 2
- 239000007789 gas Substances 0.000 description 44
- 239000000567 combustion gas Substances 0.000 description 7
- 239000012530 fluid Substances 0.000 description 6
- WYTGDNHDOZPMIW-RCBQFDQVSA-N alstonine Natural products C1=CC2=C3C=CC=CC3=NC2=C2N1C[C@H]1[C@H](C)OC=C(C(=O)OC)[C@H]1C2 WYTGDNHDOZPMIW-RCBQFDQVSA-N 0.000 description 5
- 239000002826 coolant Substances 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 230000015556 catabolic process Effects 0.000 description 2
- 230000007423 decrease Effects 0.000 description 2
- 230000003247 decreasing effect Effects 0.000 description 2
- 238000006731 degradation reaction Methods 0.000 description 2
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000007689 inspection Methods 0.000 description 2
- 238000012986 modification Methods 0.000 description 2
- 230000004048 modification Effects 0.000 description 2
- 230000008646 thermal stress Effects 0.000 description 2
- 230000015572 biosynthetic process Effects 0.000 description 1
- 239000000919 ceramic Substances 0.000 description 1
- 238000007599 discharging Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000013589 supplement Substances 0.000 description 1
Images
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/12—Cooling of plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/14—Casings modified therefor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
- F01D25/125—Cooling of bearings
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
- F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/06—Fluid supply conduits to nozzles or the like
- F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/202—Heat transfer, e.g. cooling by film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/221—Improvement of heat transfer
- F05D2260/2212—Improvement of heat transfer by creating turbulence
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Definitions
- the field of the disclosure relates generally to cooling systems and, more specifically, to impingement cooling of rotary machine components.
- energy extracted from a gas stream in a turbine is used to power a mechanical load.
- various hot gas path components may be subjected to a high-temperature gas stream. Over time, continued exposure to high temperatures may induce wear in the hot gas path components.
- air is pressurized in a compressor and mixed with fuel in a combustor to generate high-temperature gases.
- higher temperature gases increase performance, efficiency, and power output of the rotary machine.
- at least some known hot gas path components are cooled. However, higher temperature gases can also increase thermal stresses and/or thermal degradation of the rotary machine components.
- Some known hot gas path components are formed with an endwall that includes an internal cooling system, wherein a cooling fluid, such as bleed air extracted from a compressor or steam, is forced through cores defined within the endwall.
- a cooling fluid such as bleed air extracted from a compressor or steam
- At least some known cores are formed with an inlet opening that channels the cooling fluid into the core and directs the cooling fluid to impinge on internal surfaces of the core, thus increasing cooling of the endwall.
- at least some known cores include a pin bank that channels the cooling fluid directly to at least one exit opening from the inlet opening rather than channeling the cooling fluid in a circuit through the endwall.
- the cores are not as efficiently cooled as cores that include serpentine or circuitous passages.
- at least some known cores have serpentine or circuitous passages that channel the cooling fluid through the endwall from a single inlet.
- modulating the pressure drop within the passages can be difficult in known cores.
- a core for use in cooling a component used in a rotary machine includes a passage including a first inlet portion, a second inlet portion, a divider, at least one first pass, at least one second pass, and at least one turn.
- the divider separates the first inlet portion from the second inlet portion such that the first inlet portion, the second inlet portion, and the divider define a split pass inlet.
- the at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet.
- the at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction.
- the at least one turn changes a direction of flow of the cooling fluid from the first direction to the second direction.
- the at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage defines a serpentine passage.
- a gas turbine system in another aspect, includes a turbine section including an inner endwall, an outer endwall, a plurality of airfoils, and a core.
- the turbine section is coupled in flow communication with a combustion system.
- the inner endwall circumscribes the longitudinal axis of the gas turbine system.
- the outer endwall circumscribes a longitudinal axis of the gas turbine system and the inner endwall.
- the plurality of airfoils each extend between the outer endwall and the inner endwall.
- the core is positioned within at least one of the outer endwall and the inner endwall for cooling at least one of the outer endwall and the inner endwall.
- the core includes a passage including a first inlet portion, a second inlet portion, a divider, at least one first pass, at least one second pass, and at least one turn.
- the divider separates the first inlet portion from the second inlet portion such that the first inlet portion, the second inlet portion, and the divider define a split pass inlet.
- the at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet.
- the at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction.
- the at least one turn changes a direction of flow of the cooling fluid from the first direction to the second direction.
- the at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage defines a serpentine passage.
- a method of cooling a component of a rotary machine includes inserting a core into a plenum within the component.
- the core includes a passage including an inlet portion, at least one first pass, at least one second pass, at least one turn.
- the inlet portion includes a first inlet portion, a second inlet portion, and a divider.
- the divider separates the first inlet portion from the second inlet portion such that the inlet portion is a split pass inlet.
- the method also includes channeling a flow of cooling fluid into the first inlet portion and the second inlet portion.
- the method further includes channeling the flow of cooling fluid from the first inlet portion and the second inlet portion into the at least one first pass.
- the flow of cooling fluid from the first inlet portion merges with the flow of cooling fluid from the second inlet portion, and the at least one first pass channels the flow of cooling fluid in a first direction.
- the method also includes channeling the flow of cooling fluid from the at least one first pass into the at least one turn.
- the at least one turn changes a direction of flow of the cooling fluid from the first direction to a second direction opposite the first direction.
- the method further includes channeling the flow of cooling fluid from the at least one turn into the at least one second pass.
- the at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage defines a serpentine passage.
- FIG. 1 is a schematic view of an exemplary rotary machine
- FIG. 2 is an enlarged schematic view of an exemplary turbine stage of the rotary machine shown in FIG. 1 ;
- FIG. 3 is a perspective view of an exemplary stationary airfoil, outer endwall, and inner endwall that may be used with the turbine shown in FIG. 2 ;
- FIG. 4 is a perspective top view of the stationary airfoil, outer endwall, and inner endwall shown in FIG. 2 and exemplary cores extending through transparent outer and inner endwalls;
- FIG. 5 is a radial top sectional view of the outer endwall shown in FIG. 4 ;
- FIG. 6 is a radial top view of the exemplary core shown in FIGS. 3-5 ;
- FIG. 7 is a flow diagram of an exemplary method of cooling an endwall, such as the endwall, shown in FIGS. 2-6 .
- approximating language such as “generally,” “substantially,” and “about,” as used herein indicates that the term so modified may apply to only an approximate degree, as would be recognized by one of ordinary skill in the art, rather than to an absolute or perfect degree. Accordingly, a value modified by a term or terms such as “about,” “approximately,” and “substantially” is 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.
- range limitations may be identified. Such ranges may be combined and/or interchanged and include all the sub-ranges contained therein unless context or language indicates otherwise.
- first ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇ ⁇
- the terms “axial” and “axially” refer to directions and orientations extending substantially parallel to a longitudinal axis of a rotary machine.
- the terms “radial” and “radially” refer to directions and orientations extending substantially perpendicular to the longitudinal axis of the rotary machine.
- the terms “circumferential” and “circumferentially” refer to directions and orientations extending arcuately about the longitudinal axis of the rotary machine.
- the term “upstream” refers to a forward or inlet end of a rotary machine
- the term “downstream” refers to an aft or exhaust end of the rotary machine.
- a rotary component includes an outer endwall formed in a nozzle of a turbine section within the rotary machine.
- the outer endwall includes a core for use in cooling the outer endwall.
- the core includes a serpentine passage including an inlet portion, a first pass, a second pass, and a turn.
- the inlet portion includes a divider, a first inlet portion, and a second inlet portion. The divider separates the first inlet portion from the second inlet portion, such that a split pass inlet is defined.
- the first pass, the second pass, and the turn include a plurality of outlets that channel cooling fluid from the core into the hot gas path to form a cooling film on the outer endwall.
- a plurality of core ties channels cooling fluid from an upstream portion of the core to a downstream portion of the core to enable the downstream portions to be replenished with lower temperature cooling fluid.
- cooling fluid is channeled through the first pass, the second pass, and the turn to facilitate cooling the outer endwall from within the core.
- the serpentine configuration of the first pass, the second pass, and the turn enables the cooling fluid to cool a larger area of the outer endwall, thus increasing the overall heat transfer between the cooling fluid and the outer endwall.
- the serpentine configuration enables the cooling fluid to circulate with a lower pressure that is substantially equal to the pressure of combustion gases at a throat of the nozzle.
- a width of each of the first pass, the second pass, and the turn is selected to facilitate modification of, or tune, the pressure drop of the cooling fluid through the first pass, the second pass, and the turn and to increase the overall heat transfer between the cooling fluid and the outer endwall.
- outlets channel cooling fluid into the hot gas path to facilitate forming a cooling film across the stator endwall.
- core ties replenish downstream portions of the core with cooling fluid, as well as provide inspection access, rigidity during core formation, and leachability for ceramic core removal after the casing process.
- FIG. 1 is a schematic view of an exemplary rotary machine 100 , i.e., a turbomachine, and more specifically a turbine engine.
- rotary machine 100 is a gas turbine engine.
- rotary machine may be any other turbine engine and/or rotary machine, including, without limitation, a steam turbine engine, a gas turbofan aircraft engine, other aircraft engine, a wind turbine, a compressor, and a pump.
- gas turbine engine 100 includes an intake section 102 , a compressor section 104 that is coupled downstream from intake section 102 , a combustor section 106 that is coupled downstream from compressor section 104 , a turbine section 108 that is coupled downstream from combustor section 106 , and an exhaust section 110 that is coupled downstream from turbine section 108 .
- Turbine section 108 is coupled to compressor section 104 via a rotor shaft 112 .
- combustor section 106 includes a plurality of combustors 114 .
- Combustor section 106 is coupled to compressor section 104 such that each combustor 114 is in flow communication with the compressor section 104 .
- Rotor shaft 112 is further coupled to a load 116 such as, but not limited to, an electrical generator and/or a mechanical drive application.
- each of compressor section 104 and turbine section 108 includes at least one rotor assembly 118 that is coupled to rotor shaft 112 .
- intake section 102 channels air 120 towards compressor section 104 .
- Compressor section 104 compresses inlet air 120 to higher pressures prior to discharging compressed air 122 towards combustor section 106 .
- Compressed air 122 is channeled to combustor section 106 where it is mixed with fuel (not shown) and burned to generate high temperature combustion gases 124 .
- Combustion gases 124 are channeled downstream towards turbine section 108 and impinge upon turbine blades (not shown), converting thermal energy to mechanical rotational energy that is used to drive rotor assembly 118 about a longitudinal axis 126 .
- combustor section 106 and turbine section 108 are referred to as a hot gas section of turbine engine 100 .
- Exhaust gases 128 then discharge through exhaust section 110 to ambient atmosphere or to a steam turbine (not shown), if the rotary machine 100 is a gas turbine that is part of a combined cycle power plant.
- FIG. 2 is an enlarged schematic view of an exemplary turbine stage 200 of turbine engine 100 (shown in FIG. 1 ).
- Stage 200 includes a plurality of radially-extending stationary airfoils 202 circumferentially-spaced about longitudinal axis 126 , and a plurality of radially-extending rotating airfoils 204 that are downstream from stationary airfoils 202 and circumferentially-spaced around longitudinal axis 126 .
- the radial direction is indicated by arrow 218 .
- Each rotating airfoil 204 is coupled to rotor shaft 112 (shown in FIG. 1 ) via a disk 230 and extends radially outward towards a casing 208 .
- each stationary airfoil 202 extends from a first end 216 coupled to an outer endwall 207 of casing 208 of turbine section 108 , radially inward to a second end 214 coupled to an inner endwall 209 along a radial direction 218 (the outer endwall 208 and the inner endwall 209 being shown in FIG. 3 ). Additionally, each stationary airfoil 202 extends axially from a leading edge 222 downstream to an opposing trailing edge 224 .
- outer endwall 207 and inner endwall 209 define the radial boundaries of a hot gas flow path 232 , such that a flow of high temperature combustion gases 124 is channeled therethrough, exposing surfaces of outer endwall 207 and inner endwall 209 to high temperatures and potential thermal stresses and/or thermal degradation.
- an interior cavity or plenum 236 is defined within outer endwall 207 and inner endwall 209 to facilitate internal impingement cooling of an interior surface of outer endwall 207 and inner endwall 209 .
- Plenum 236 is in flow communication with a coolant supply channel 233 via a plenum inlet 234 defined in outer endwall 207 and inner endwall 209 .
- coolant supply channel 233 channels a cooling fluid 240 , such as a flow of pressurized bleed air from compressor section 104 (shown in FIG. 1 ), towards plenum inlet 234 .
- cooling fluid 240 may be any suitable fluid other than air.
- stage 200 is a first stage of turbine section 108 , and stationary airfoils 202 , outer endwall 207 , and inner endwall 209 define a first stage turbine nozzle that is immediately downstream from combustor section 106 (shown in FIG. 1 ).
- stage 200 is any other stage of turbine section 108 .
- plenum 236 extends axially aftward into outer endwall 207 and inner endwall 209 .
- FIG. 3 is a perspective view of stationary airfoil 202 , outer endwall 207 , and inner endwall 209 and illustrates exemplary cores 300 extending through transparent outer endwall 207 and inner endwall 209 .
- FIG. 4 is a perspective top view of stationary airfoil 202 , outer endwall 207 , and inner endwall 209 .
- FIG. 5 is a radial top sectional view of an exemplary outer endwall 207 .
- FIG. 6 is a radial top view of an exemplary core 300 .
- core 300 is defined in plenum 236 of outer endwall 207 and inner endwall 209 for cooling outer endwall 207 and inner endwall 209 . More specifically, cores 300 are disposed within outer endwall 207 and inner endwall 209 to facilitate cooling outer endwall 207 and inner endwall 209 with cooling fluid 240 .
- stationary airfoils 202 each include a suction side wall 302 and a pressure side wall 304 (shown in FIG. 5 ). Adjacent stationary airfoils 202 , outer endwall 207 , and inner endwall 209 define a throat 306 (shown in FIG. 5 ) where a velocity of combustion gases 124 is maximized.
- Outer endwall 207 includes an upstream portion 308 that is upstream from stationary airfoils 202 and a downstream portion 310 that is downstream from stationary airfoils 202 .
- Outer endwall 207 also includes a trailing edge 312 adjacent to rotating airfoils 204 .
- core 300 is defined within outer endwall 207 downstream from suction side wall 302 .
- core 300 may be positioned within outer endwall 207 such that an upstream portion 314 (shown in FIG. 5 ) of core 300 is upstream from throat 306 and a downstream portion 316 of core 300 is downstream from throat 306 .
- core 300 may be positioned within outer endwall 207 such that core 300 facilitates cooling outer endwall 207 and trailing edge 312 .
- core 300 includes at least one passage 600 .
- passage 600 is a serpentine passage that channels cooling fluid 240 adjacent to outer endwall 207 and inner endwall 209 to facilitate cooling outer endwall 207 and inner endwall 209 .
- a similar serpentine passage 600 may be used to channel cooling fluid 240 adjacent to inner endwall 209 to facilitate cooling inner endwall 209 .
- a “serpentine passage” is a conduit with at least one turn such that the passage winds or twists. That is, the serpentine passage does not have only a substantially straight path from the inlet to the outlet.
- serpentine passage 600 includes at least one inlet 602 and 604 , an first inlet portion 606 and a second inlet portion 608 forming a split pass inlet region 610 , a first pass 612 , a second pass 614 , at least one turn 616 disposed between first pass 612 and second pass 614 , and at least one outlet 618 .
- First pass 612 , second pass 614 , and turn 616 are oriented such that passage 600 is a serpentine passage.
- serpentine passage 600 includes a plurality of inlets 602 and 604 .
- Inlets 602 and 604 receive cooling fluid 240 from coolant supply channel 233 ( FIG. 2 ) and channel cooling fluid 240 to first inlet portion 606 and second inlet portion 608 .
- at least one first inlet 602 channels cooling fluid 240 to first inlet portion 606
- at least one second inlet 604 channels cooling fluid 240 to second inlet portion 608 .
- FIG. 6 shows a single inlet 602 and 604 extending into each inlet portion 606 and 608 .
- each inlet portion 606 and 608 may include a plurality of inlets 602 and 604 .
- serpentine passage 600 may include more than two inlet portions 606 and 608 .
- first inlets 602 may include two to twenty first inlets 602 channeling cooling fluid 240 to first inlet portion 606
- second inlets 604 may include two to twenty second inlets 604 channeling cooling fluid 240 to second inlet portion 608 .
- first inlets 602 may include eight to ten first inlets 602 channeling cooling fluid 240 to first inlet portion 606
- second inlets 604 may include eight to ten second inlets 604 channeling cooling fluid 240 to second inlet portion 608 .
- a divider 620 separates first inlet portion 606 from second inlet portion 608 to form split pass inlet region 610 .
- Divider 620 reduces a width 622 of split pass inlet region 610 such that a velocity of cooling fluid 240 through split pass inlet region 610 is increased. More specifically, the velocity of cooling fluid 240 through split pass inlet region 610 without divider 620 would decrease because width 622 of split pass inlet region 610 increases downstream from inlets 602 and 604 .
- Divider 620 decreases width 622 such that the velocity of cooling fluid 240 either remains constant or increases as cooling fluid 240 is channeled through split pass inlet region 610 .
- first inlet portion 606 defines a first width 624
- second inlet portion 608 defines a second width 626 .
- First width 624 may be the same or different than second width 626
- first width 624 and second width 626 may be selectively sized to enable a specific volume of cooling fluid 240 to be channeled through passage 600 .
- first width 624 and second width 626 may be sized for a specific volumetric flow of cooling fluid 240 such that a heat transfer coefficient of cooling fluid 240 is tuned to the specific heat transfer requirements of outer endwall 207 and/or inner endwall 209 .
- First pass 612 extends through outer endwall 207 substantially parallel to trailing edge 312 and second pass 614 .
- First pass 612 defines a third width 628 which, along with first width 624 and second width 626 , may be selectively sized to enable a specific volumetric flow of cooling fluid 240 to flow therethrough such that a heat transfer coefficient of cooling fluid 240 is tuned to the specific heat transfer requirements of outer endwall 207 and/or inner endwall 209 .
- First pass 612 receives cooling fluid 240 from first inlet portion 606 and second inlet portion 608 and channels cooling fluid 240 to turn 616 .
- Turn 616 receives cooling fluid 240 from first pass 612 and channels cooling fluid 240 to second pass 614 .
- First pass 612 , second pass 614 , and turn 616 are oriented such that first pass 612 channels cooling fluid 240 in a first direction 630 , and second pass 614 channels cooling fluid 240 in a second direction 632 opposite first direction 630 .
- Turn 616 changes a direction of flow of cooling fluid 240 from first direction 630 to second direction 632 .
- turn 616 is a 180° turn such that first direction 630 is diametrically opposite second direction 632 .
- first pass 612 , second pass 614 , and turn 616 may be oriented such that first pass 612 and second pass 614 have any orientation that enables core 300 to operate as described herein.
- Turn 616 receives cooling fluid 240 from first pass 612 , changes the direction of flow of cooling fluid 240 , and channels cooling fluid 240 to second pass 614 .
- Second pass 614 extends through outer endwall 207 substantially parallel to trailing edge 312 and to first pass 612 .
- Second pass 614 defines a fourth width 634 which, along with first width 624 , second width 626 , and third width 628 , may be selectively sized to enable a specific volumetric flow of cooling fluid 240 such that a heat transfer coefficient of cooling fluid 240 is tuned to the specific heat transfer requirements of outer endwall 207 and/or inner endwall 209 .
- Second pass 614 receives cooling fluid 240 from turn 616 and channels cooling fluid 240 to outlets 618 .
- core 300 includes a single first pass 612 , a single second pass 614 , and a single turn 616 .
- core 300 may include any number of passes and/or turns that enables core 300 to operate as described herein.
- core 300 may include three passes and two turns.
- core 300 may include four passes and three turns.
- Core 300 includes at least one outlet 618 downstream from throat 306 . While core 300 may include only a single outlet 618 , in the exemplary embodiment, core 300 includes a plurality of outlets 618 that channel cooling fluid from core 300 into hot gas flow path 232 .
- core 300 may include at least one first outlet 636 that extends from first pass 612 through outer endwall 207 and into hot gas flow path 232 .
- core 300 includes a plurality of first outlets 636 , each of which extends from first pass 612 through outer endwall 207 and into hot gas flow path 232 . Cooling fluid 240 discharged into hot gas flow path 232 from first outlets 636 may form a cooling film (not shown) on outer endwall 207 that protects outer endwall 207 .
- Core 300 may also include at least one second outlet 638 that extends from second pass 614 through outer endwall 207 and into hot gas flow path 232 .
- core 300 includes a plurality of second outlets 638 , each of which extends from second pass 614 through outer endwall 207 and into hot gas flow path 232 .
- Cooling fluid 240 discharged into hot gas flow path 232 from second outlets 638 may form a cooling film (not shown) on outer endwall 207 that facilitates protecting outer endwall 207 .
- Core 300 may further include at least one third outlet 640 (shown in FIG. 4 ) that extends from second pass 614 through trailing edge 312 of inner endwall 209 and into hot gas flow path 232 .
- core 300 includes a plurality of third outlets 640 , each of which extends from second pass 614 through trailing edge 312 of outer endwall 207 and into hot gas flow path 232 .
- Cooling fluid 240 discharged into hot gas flow path 232 from third outlets 640 may form a cooling film (not shown) on trailing edge 312 of outer endwall 207 that protects trailing edge 312 of outer endwall 207 .
- Core 300 may also include at least one fourth outlet 642 that extends from turn 616 through outer endwall 207 and into hot gas flow path 232 .
- core 300 includes a plurality of fourth outlets 642 , each of which extends from turn 616 through trailing edge 312 of outer endwall 207 and into hot gas flow path 232 .
- Cooling fluid 240 discharged into hot gas flow path 232 from fourth outlets 642 may form a cooling film (not shown) on outer endwall 207 that facilitates protecting outer endwall 207 .
- Core 300 may include outlets 218 in any location that enables core 300 to operate as described herein.
- first, second, third, and fourth outlets 636 , 638 , 640 , and 642 may be sized and arranged to facilitate tuning to a specific/desired pressure drop, volumetric flow rate, and/or heat transfer coefficient of cooling fluid 240 .
- first outlets 636 may have a first size
- second outlets 638 may be sized with a second size that is smaller than the first size of first outlets 636 .
- first outlets 636 form a cooling film (not shown) on outer endwall 207
- second outlets 638 supplement the cooling film with additional cooling fluid 240 .
- outlets 636 , 638 , 640 , and 642 facilitate reducing the volumetric flow of cooling fluid 240 through passage 600 and facilitate reducing the pressure drop of cooling fluid 240 through passage 600 .
- the size, shape, and position of first, second, third, and fourth outlets 636 , 638 , 640 , and 642 may be sized and arranged to facilitate tuning the pressure drop, the volumetric flow rate, and/or the heat transfer coefficient of cooling fluid 240 .
- first pass 612 and second pass 614 each include a plurality of turbulators or ridges 644 that create turbulence within first pass 612 and second pass 614 .
- turbulators 644 create turbulent flow within cooling fluid 240 to facilitate increasing the heat transfer coefficient of cooling fluid 240 within first pass 612 and second pass 614 .
- Increasing the heat transfer coefficient increases the overall heat transfer between cooling fluid 240 and outer endwall 207 .
- turbulators 644 have a height (not shown) that is about 10% that of third width 628 and fourth width 634 .
- turbulators 644 may have any other height that enables core 300 to operate as described herein.
- core 300 includes a plurality of hollow core ties 646 that extend from either first inlet portion 606 to second inlet portion 608 or first pass 612 to second pass 614 .
- core 300 includes at least one first core tie 648 that extends from first inlet portion 606 to second inlet portion 608 and at least one second core tie 650 extending from first pass 612 to second pass 614 .
- core 300 includes a single first core tie 648 and a plurality of second core ties 650 .
- First and second core ties 648 and 650 which define fluid passages therein, replenish downstream portions of passage 600 with cooling fluid 240 .
- cooling fluid 240 As cooling fluid 240 is channeled through passage 600 , a temperature of cooling fluid 240 increases which facilitates decreasing the heat transfer coefficient of cooling fluid 240 and decreasing the overall heat transfer between cooling fluid 240 and outer endwall 207 .
- Core ties 646 are “short cuts” that channel cooling fluid 240 from upstream portions of passage 600 to downstream portions of passage 600 without heat transfer between cooling fluid 240 and outer endwall 207 . As such, cooling fluid 240 that is channeled through core ties 646 has a lower temperature than cooling fluid 240 that was channeled through first pass 612 , second pass 614 , and turn 616 .
- core ties 646 replenish downstream portions of passage 600 with cooling fluid 240 that has a lower temperature, which facilitates increasing the heat transfer coefficient of cooling fluid 240 and overall heat transfer between cooling fluid 240 and outer endwall 207 .
- Core ties 646 may also be used as inspection ports to inspect core 300 .
- inlets 602 and 604 receive cooling fluid 240 from coolant supply channel 233 and channel cooling fluid 240 to first inlet portion 606 and second inlet portion 608 .
- First inlet portion 606 channels a portion of cooling fluid 240 through first core tie 648 to replenish second inlet portion 608 .
- First inlet portion 606 and second inlet portion 608 merge into first pass 612 and each channels cooling fluid 240 into first pass 612 .
- First pass 612 channels a portion of cooling fluid 240 through second core ties 650 to replenish second pass 614 and channels another portion of cooling fluid 240 to turn 616 .
- First pass 612 also channels a portion of cooling fluid through first outlet 636 into hot gas path 232 to form a cooling film on outer endwall 207 .
- Turn 616 channels a portion of cooling fluid 240 through fourth outlet 642 into hot gas path 232 to form the cooling film on outer endwall 207 and channels the remaining cooling fluid 240 to second pass 614 .
- Second pass 614 channels cooling fluid 240 through second and third outlets 638 and 640 to replenish the cooling film and to form a cooling film on trailing edge 312 .
- Cooling fluid 240 exchanges heat with outer endwall 207 as it is channeled through passage 600 . As such, cooling fluid 240 facilitates cooling outer endwall 207 from within core 300 and forms a protective cooling film that protects outer endwall 207 .
- the serpentine configuration of passage 600 enables cooling fluid 240 to cool a larger area of outer endwall 207 , thus increasing the overall heat transfer between cooling fluid 240 and outer endwall 207 .
- the serpentine orientation of passage 600 enables cooling fluid 240 to have a lower pressure that is approximately equal to the pressure of combustion gases 124 at throat 306 .
- widths 624 , 626 , 628 , and 634 are sized to tune the pressure drop of cooling fluid 240 through passage 600 and to facilitate increasing the overall heat transfer between cooling fluid 240 and outer endwall 207 .
- outlets 618 channel cooling fluid 240 into hot gas path 232 to protect outer endwall 207 by forming a cooling film.
- core ties 646 replenish downstream portions of passage 600 with cooling fluid 240 . Accordingly, the arrangement of core 300 increases the overall heat transfer between cooling fluid 240 and outer endwall 207 .
- FIGS. 3 through 6 has described core 300 and its features in connection with outer endwall 207 , it should be understood that the core 300 may be employed with similar features in inner endwall 209 to achieve similar results and benefits.
- FIG. 7 is a flow diagram of an exemplary method 700 of cooling a component of a rotary machine.
- method 700 includes inserting 702 a core into a plenum within the component.
- the core includes a passage including an inlet portion, at least one first pass, at least one second pass, at least one turn between respective first pass(es) and second pass(es).
- the inlet portion includes a divider that separates a first inlet portion from a second inlet portion, such that the inlet portion is a split pass inlet.
- Method 700 also includes channeling 704 a flow of cooling fluid into the first inlet portion and the second inlet portion.
- Method 700 further includes channeling 706 the flow of cooling fluid from the first inlet portion and the second inlet portion into the at least one first pass.
- the flow of cooling fluid from the first inlet portion merges with the flow of cooling fluid from the second inlet portion, and the at least one first pass channels the flow of cooling fluid in a first direction.
- Method 700 also includes channeling 708 the flow of cooling fluid from the at least one first pass into the at least one turn.
- the at least one turn changes a direction of flow of the cooling fluid from the first direction to a second direction opposite the first direction.
- Method 700 further includes channeling 710 the flow of cooling fluid from the at least one turn into the at least one second pass.
- the at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage is a serpentine passage.
- a rotary component includes an outer endwall formed in a nozzle of a turbine section within the rotary machine.
- the outer endwall includes a core for use in cooling the outer endwall.
- the core includes a serpentine passage including an inlet portion, a first pass, a second pass, and a turn between the first pass and the second pass.
- the inlet portion includes a divider that separates a first inlet portion from a second inlet portion, such that a split pass inlet is defined.
- the first pass, the second pass, and the turn include a plurality of outlets, each of which channels cooling fluid from the core into the hot gas path to form a cooling film on the outer endwall.
- a plurality of hollow core ties channels cooling fluid from an upstream portion of the core to a downstream portion of the core to enable the downstream portions to be replenished with lower temperature cooling fluid.
- cooling fluid is channeled through the first pass, the second pass, and the turn to facilitate convective cooling of the outer endwall from within the core.
- the serpentine configuration of the first pass, the second pass, and the turn enables the cooling fluid to convectively cool a larger area of the outer endwall, thus increasing the overall heat transfer between the cooling fluid and the outer endwall. Additionally, the serpentine configuration enables the cooling fluid to circulate with a lower pressure that is substantially equal to the pressure of combustion gases at a throat of the nozzle.
- a width of each of the first pass, the second pass, and the turn is selected to facilitate modification of, or tune, the pressure drop of the cooling fluid through the first pass, the second pass, and the turn and to increase the overall heat transfer between the cooling fluid and the outer endwall.
- the outlets channel cooling fluid into the hot gas path to facilitate forming a cooling film across the stator endwall.
- the core ties replenish downstream portions of the core with cooling fluid.
- an exemplary technical effect of the systems and methods described herein includes at least one of: (a) removing heat from a rotary machine component; (b) increasing the heat transfer coefficient of a cooling fluid; (c) increasing the overall heat transfer between the cooling fluid and the rotary machine component; and (d) increasing rotary machine efficiency.
- Exemplary embodiments of systems and methods for cooling portions of a hot gas path of a rotary machine are described above in detail.
- the methods and systems 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.
- the method may also be used in combination with other turbine components, and are not limited to practice only with the portions of the hot gas path of the rotary machine as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many other rotary machine applications.
Abstract
A core for use in cooling a component used in a rotary machine is provided. The core includes a passage including a divider separating a first inlet portion and a second inlet portion to define a split pass inlet, which is fluidly coupled to at least one first pass, at least one second pass, and at least one turn. The at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet. The at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a direction of flow of the cooling fluid from the first direction to the second direction. The at least one first pass, the at least one second pass, and the at least one turn are arranged, such that the passage defines a serpentine passage.
Description
- The field of the disclosure relates generally to cooling systems and, more specifically, to impingement cooling of rotary machine components.
- In at least some known rotary machines, energy extracted from a gas stream in a turbine is used to power a mechanical load. During operation of the rotary machine, various hot gas path components may be subjected to a high-temperature gas stream. Over time, continued exposure to high temperatures may induce wear in the hot gas path components. For example, in some known turbines, air is pressurized in a compressor and mixed with fuel in a combustor to generate high-temperature gases. Generally, higher temperature gases increase performance, efficiency, and power output of the rotary machine. To facilitate reducing the effects of the high temperatures, at least some known hot gas path components are cooled. However, higher temperature gases can also increase thermal stresses and/or thermal degradation of the rotary machine components.
- Some known hot gas path components are formed with an endwall that includes an internal cooling system, wherein a cooling fluid, such as bleed air extracted from a compressor or steam, is forced through cores defined within the endwall. At least some known cores are formed with an inlet opening that channels the cooling fluid into the core and directs the cooling fluid to impinge on internal surfaces of the core, thus increasing cooling of the endwall. However, at least some known cores include a pin bank that channels the cooling fluid directly to at least one exit opening from the inlet opening rather than channeling the cooling fluid in a circuit through the endwall. As such, the cores are not as efficiently cooled as cores that include serpentine or circuitous passages. Moreover, at least some known cores have serpentine or circuitous passages that channel the cooling fluid through the endwall from a single inlet. However, modulating the pressure drop within the passages can be difficult in known cores.
- In one aspect, a core for use in cooling a component used in a rotary machine is provided. The core includes a passage including a first inlet portion, a second inlet portion, a divider, at least one first pass, at least one second pass, and at least one turn. The divider separates the first inlet portion from the second inlet portion such that the first inlet portion, the second inlet portion, and the divider define a split pass inlet. The at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet. The at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a direction of flow of the cooling fluid from the first direction to the second direction. The at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage defines a serpentine passage.
- In another aspect, a gas turbine system is provided. The gas turbine system includes a turbine section including an inner endwall, an outer endwall, a plurality of airfoils, and a core. The turbine section is coupled in flow communication with a combustion system. The inner endwall circumscribes the longitudinal axis of the gas turbine system. The outer endwall circumscribes a longitudinal axis of the gas turbine system and the inner endwall. The plurality of airfoils each extend between the outer endwall and the inner endwall. The core is positioned within at least one of the outer endwall and the inner endwall for cooling at least one of the outer endwall and the inner endwall. The core includes a passage including a first inlet portion, a second inlet portion, a divider, at least one first pass, at least one second pass, and at least one turn. The divider separates the first inlet portion from the second inlet portion such that the first inlet portion, the second inlet portion, and the divider define a split pass inlet. The at least one first pass channels a flow of cooling fluid in a first direction from the split pass inlet. The at least one second pass channels the flow of cooling fluid in a second direction opposite the first direction. The at least one turn changes a direction of flow of the cooling fluid from the first direction to the second direction. The at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage defines a serpentine passage.
- In another aspect, a method of cooling a component of a rotary machine is provided. The method includes inserting a core into a plenum within the component. The core includes a passage including an inlet portion, at least one first pass, at least one second pass, at least one turn. The inlet portion includes a first inlet portion, a second inlet portion, and a divider. The divider separates the first inlet portion from the second inlet portion such that the inlet portion is a split pass inlet. The method also includes channeling a flow of cooling fluid into the first inlet portion and the second inlet portion. The method further includes channeling the flow of cooling fluid from the first inlet portion and the second inlet portion into the at least one first pass. The flow of cooling fluid from the first inlet portion merges with the flow of cooling fluid from the second inlet portion, and the at least one first pass channels the flow of cooling fluid in a first direction. The method also includes channeling the flow of cooling fluid from the at least one first pass into the at least one turn. The at least one turn changes a direction of flow of the cooling fluid from the first direction to a second direction opposite the first direction. The method further includes channeling the flow of cooling fluid from the at least one turn into the at least one second pass. The at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage defines a serpentine passage.
- 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 view of an exemplary rotary machine; -
FIG. 2 is an enlarged schematic view of an exemplary turbine stage of the rotary machine shown inFIG. 1 ; -
FIG. 3 is a perspective view of an exemplary stationary airfoil, outer endwall, and inner endwall that may be used with the turbine shown inFIG. 2 ; -
FIG. 4 is a perspective top view of the stationary airfoil, outer endwall, and inner endwall shown inFIG. 2 and exemplary cores extending through transparent outer and inner endwalls; -
FIG. 5 is a radial top sectional view of the outer endwall shown inFIG. 4 ; -
FIG. 6 is a radial top view of the exemplary core shown inFIGS. 3-5 ; and -
FIG. 7 is a flow diagram of an exemplary method of cooling an endwall, such as the endwall, shown inFIGS. 2-6 . - 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.
- 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.
- Unless otherwise indicated, approximating language, such as “generally,” “substantially,” and “about,” as used herein indicates that the term so modified may apply to only an approximate degree, as would be recognized by one of ordinary skill in the art, rather than to an absolute or perfect degree. Accordingly, a value modified by a term or terms such as “about,” “approximately,” and “substantially” is 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 identified. Such ranges may be combined and/or interchanged and include all the sub-ranges contained therein unless context or language indicates otherwise. Additionally, unless otherwise indicated, the terms “first,” “second,” etc. are used herein merely as labels, and are not intended to impose ordinal, positional, or hierarchical requirements on the items to which these terms refer. Moreover, reference to, for example, a “second” item does not require or preclude the existence of, for example, a “first” or lower-numbered item or a “third” or higher-numbered item.
- As used herein, the terms “axial” and “axially” refer to directions and orientations extending substantially parallel to a longitudinal axis of a rotary machine. Moreover, the terms “radial” and “radially” refer to directions and orientations extending substantially perpendicular to the longitudinal axis of the rotary machine. In addition, as used herein, the terms “circumferential” and “circumferentially” refer to directions and orientations extending arcuately about the longitudinal axis of the rotary machine. Further, as used herein, the term “upstream” refers to a forward or inlet end of a rotary machine, and the term “downstream” refers to an aft or exhaust end of the rotary machine. When discussing a flow of fluid through a component, the direction from which the fluid flows is described as “upstream,” and the direction in which the fluid flows is described as “downstream.”
- The systems described herein relate to a serpentine core for use in cooling portions of a hot gas path in a rotary machine. Specifically, in the exemplary embodiment, a rotary component includes an outer endwall formed in a nozzle of a turbine section within the rotary machine. The outer endwall includes a core for use in cooling the outer endwall. The core includes a serpentine passage including an inlet portion, a first pass, a second pass, and a turn. The inlet portion includes a divider, a first inlet portion, and a second inlet portion. The divider separates the first inlet portion from the second inlet portion, such that a split pass inlet is defined. The first pass, the second pass, and the turn include a plurality of outlets that channel cooling fluid from the core into the hot gas path to form a cooling film on the outer endwall. A plurality of core ties channels cooling fluid from an upstream portion of the core to a downstream portion of the core to enable the downstream portions to be replenished with lower temperature cooling fluid.
- In the exemplary embodiment, cooling fluid is channeled through the first pass, the second pass, and the turn to facilitate cooling the outer endwall from within the core. The serpentine configuration of the first pass, the second pass, and the turn enables the cooling fluid to cool a larger area of the outer endwall, thus increasing the overall heat transfer between the cooling fluid and the outer endwall. Additionally, the serpentine configuration enables the cooling fluid to circulate with a lower pressure that is substantially equal to the pressure of combustion gases at a throat of the nozzle. Furthermore, a width of each of the first pass, the second pass, and the turn is selected to facilitate modification of, or tune, the pressure drop of the cooling fluid through the first pass, the second pass, and the turn and to increase the overall heat transfer between the cooling fluid and the outer endwall. Moreover, the outlets channel cooling fluid into the hot gas path to facilitate forming a cooling film across the stator endwall. Additionally, the core ties replenish downstream portions of the core with cooling fluid, as well as provide inspection access, rigidity during core formation, and leachability for ceramic core removal after the casing process.
-
FIG. 1 is a schematic view of an exemplaryrotary machine 100, i.e., a turbomachine, and more specifically a turbine engine. In the exemplary embodiment,rotary machine 100 is a gas turbine engine. Alternatively, rotary machine may be any other turbine engine and/or rotary machine, including, without limitation, a steam turbine engine, a gas turbofan aircraft engine, other aircraft engine, a wind turbine, a compressor, and a pump. In the exemplary embodiment,gas turbine engine 100 includes anintake section 102, acompressor section 104 that is coupled downstream fromintake section 102, acombustor section 106 that is coupled downstream fromcompressor section 104, aturbine section 108 that is coupled downstream fromcombustor section 106, and anexhaust section 110 that is coupled downstream fromturbine section 108.Turbine section 108 is coupled tocompressor section 104 via arotor shaft 112. - It should be noted that, as used herein, the term “couple” is not limited to a direct mechanical, thermal, electrical, and/or flow communication connection between components, but may also include an indirect mechanical, thermal, electrical, and/or flow communication connection between multiple components. In the exemplary embodiment,
combustor section 106 includes a plurality ofcombustors 114.Combustor section 106 is coupled tocompressor section 104 such that each combustor 114 is in flow communication with thecompressor section 104.Rotor shaft 112 is further coupled to aload 116 such as, but not limited to, an electrical generator and/or a mechanical drive application. In the exemplary embodiment, each ofcompressor section 104 andturbine section 108 includes at least onerotor assembly 118 that is coupled torotor shaft 112. - During operation,
intake section 102channels air 120 towardscompressor section 104.Compressor section 104 compressesinlet air 120 to higher pressures prior to dischargingcompressed air 122 towardscombustor section 106.Compressed air 122 is channeled tocombustor section 106 where it is mixed with fuel (not shown) and burned to generate hightemperature combustion gases 124.Combustion gases 124 are channeled downstream towardsturbine section 108 and impinge upon turbine blades (not shown), converting thermal energy to mechanical rotational energy that is used to driverotor assembly 118 about alongitudinal axis 126. Often,combustor section 106 andturbine section 108 are referred to as a hot gas section ofturbine engine 100.Exhaust gases 128 then discharge throughexhaust section 110 to ambient atmosphere or to a steam turbine (not shown), if therotary machine 100 is a gas turbine that is part of a combined cycle power plant. -
FIG. 2 is an enlarged schematic view of anexemplary turbine stage 200 of turbine engine 100 (shown inFIG. 1 ).Stage 200 includes a plurality of radially-extendingstationary airfoils 202 circumferentially-spaced aboutlongitudinal axis 126, and a plurality of radially-extendingrotating airfoils 204 that are downstream fromstationary airfoils 202 and circumferentially-spaced aroundlongitudinal axis 126. The radial direction is indicated byarrow 218. Eachrotating airfoil 204 is coupled to rotor shaft 112 (shown inFIG. 1 ) via adisk 230 and extends radially outward towards acasing 208. - In the exemplary embodiment, each
stationary airfoil 202 extends from afirst end 216 coupled to anouter endwall 207 ofcasing 208 ofturbine section 108, radially inward to asecond end 214 coupled to aninner endwall 209 along a radial direction 218 (the outer endwall 208 and theinner endwall 209 being shown inFIG. 3 ). Additionally, eachstationary airfoil 202 extends axially from aleading edge 222 downstream to an opposing trailingedge 224. During operation,outer endwall 207 andinner endwall 209 define the radial boundaries of a hotgas flow path 232, such that a flow of hightemperature combustion gases 124 is channeled therethrough, exposing surfaces ofouter endwall 207 andinner endwall 209 to high temperatures and potential thermal stresses and/or thermal degradation. To mitigate such thermal effects, an interior cavity orplenum 236 is defined withinouter endwall 207 andinner endwall 209 to facilitate internal impingement cooling of an interior surface ofouter endwall 207 andinner endwall 209. -
Plenum 236 is in flow communication with acoolant supply channel 233 via aplenum inlet 234 defined inouter endwall 207 andinner endwall 209. In the exemplary embodiment,coolant supply channel 233 channels a coolingfluid 240, such as a flow of pressurized bleed air from compressor section 104 (shown inFIG. 1 ), towardsplenum inlet 234. Alternatively, coolingfluid 240 may be any suitable fluid other than air. The term “fluid,” as used herein, includes any medium or material that flows, including, but not limited to, air or steam. In the exemplary embodiment,stage 200 is a first stage ofturbine section 108, andstationary airfoils 202,outer endwall 207, andinner endwall 209 define a first stage turbine nozzle that is immediately downstream from combustor section 106 (shown inFIG. 1 ). In alternative embodiments,stage 200 is any other stage ofturbine section 108. In the exemplary embodiment,plenum 236 extends axially aftward intoouter endwall 207 andinner endwall 209. -
FIG. 3 is a perspective view ofstationary airfoil 202,outer endwall 207, and inner endwall 209 and illustratesexemplary cores 300 extending through transparentouter endwall 207 andinner endwall 209.FIG. 4 is a perspective top view ofstationary airfoil 202,outer endwall 207, andinner endwall 209.FIG. 5 is a radial top sectional view of an exemplaryouter endwall 207.FIG. 6 is a radial top view of anexemplary core 300. As shown inFIGS. 3-5 ,core 300 is defined inplenum 236 ofouter endwall 207 andinner endwall 209 for coolingouter endwall 207 andinner endwall 209. More specifically,cores 300 are disposed withinouter endwall 207 andinner endwall 209 to facilitate coolingouter endwall 207 andinner endwall 209 with coolingfluid 240. - As shown in
FIGS. 3-5 ,stationary airfoils 202 each include asuction side wall 302 and a pressure side wall 304 (shown inFIG. 5 ). Adjacentstationary airfoils 202,outer endwall 207, andinner endwall 209 define a throat 306 (shown inFIG. 5 ) where a velocity ofcombustion gases 124 is maximized.Outer endwall 207 includes anupstream portion 308 that is upstream fromstationary airfoils 202 and adownstream portion 310 that is downstream fromstationary airfoils 202.Outer endwall 207 also includes a trailingedge 312 adjacent torotating airfoils 204. In the illustrated embodiment,core 300 is defined withinouter endwall 207 downstream fromsuction side wall 302. However,core 300 may be positioned withinouter endwall 207 such that an upstream portion 314 (shown inFIG. 5 ) ofcore 300 is upstream fromthroat 306 and adownstream portion 316 ofcore 300 is downstream fromthroat 306. Moreover,core 300 may be positioned withinouter endwall 207 such thatcore 300 facilitates coolingouter endwall 207 and trailingedge 312. - As shown in
FIG. 6 ,core 300 includes at least onepassage 600. In the exemplary embodiment ofFIG. 6 ,passage 600 is a serpentine passage that channels cooling fluid 240 adjacent toouter endwall 207 andinner endwall 209 to facilitate coolingouter endwall 207 andinner endwall 209. As shown inFIGS. 3 and 4 , a similarserpentine passage 600 may be used to channel cooling fluid 240 adjacent toinner endwall 209 to facilitate coolinginner endwall 209. As used herein, a “serpentine passage” is a conduit with at least one turn such that the passage winds or twists. That is, the serpentine passage does not have only a substantially straight path from the inlet to the outlet. Rather, the path from the inlet to the outlet makes at least one turn such that the serpentine passage does not have a straight line-of-sight path defined from the inlet to the outlet. In the exemplary embodiment,serpentine passage 600 includes at least oneinlet first inlet portion 606 and a second inlet portion 608 forming a splitpass inlet region 610, afirst pass 612, asecond pass 614, at least oneturn 616 disposed betweenfirst pass 612 andsecond pass 614, and at least oneoutlet 618. First pass 612,second pass 614, and turn 616 are oriented such thatpassage 600 is a serpentine passage. In the illustrated embodiment,serpentine passage 600 includes a plurality ofinlets -
Inlets FIG. 2 ) and channel cooling fluid 240 tofirst inlet portion 606 and second inlet portion 608. Specifically, at least onefirst inlet 602 channels cooling fluid 240 tofirst inlet portion 606, and at least onesecond inlet 604 channels cooling fluid 240 to second inlet portion 608.FIG. 6 shows asingle inlet inlet portion 606 and 608. However, eachinlet portion 606 and 608 may include a plurality ofinlets serpentine passage 600 may include more than twoinlet portions 606 and 608. For example,first inlets 602 may include two to twentyfirst inlets 602 channeling cooling fluid 240 tofirst inlet portion 606, andsecond inlets 604 may include two to twentysecond inlets 604 channeling cooling fluid 240 to second inlet portion 608. More specifically,first inlets 602 may include eight to tenfirst inlets 602 channeling cooling fluid 240 tofirst inlet portion 606, andsecond inlets 604 may include eight to tensecond inlets 604 channeling cooling fluid 240 to second inlet portion 608. - A
divider 620 separatesfirst inlet portion 606 from second inlet portion 608 to form splitpass inlet region 610.Divider 620 reduces awidth 622 of splitpass inlet region 610 such that a velocity of cooling fluid 240 through splitpass inlet region 610 is increased. More specifically, the velocity of cooling fluid 240 through splitpass inlet region 610 withoutdivider 620 would decrease becausewidth 622 of splitpass inlet region 610 increases downstream frominlets Divider 620 decreaseswidth 622 such that the velocity of cooling fluid 240 either remains constant or increases as coolingfluid 240 is channeled through splitpass inlet region 610. - Additionally,
first inlet portion 606 defines afirst width 624, and second inlet portion 608 defines asecond width 626.First width 624 may be the same or different thansecond width 626, andfirst width 624 andsecond width 626 may be selectively sized to enable a specific volume of cooling fluid 240 to be channeled throughpassage 600. More specifically,first width 624 andsecond width 626 may be sized for a specific volumetric flow of cooling fluid 240 such that a heat transfer coefficient of coolingfluid 240 is tuned to the specific heat transfer requirements ofouter endwall 207 and/orinner endwall 209. -
First inlet portion 606 and second inlet portion 608 merge intofirst pass 612, and each inlet portion channels cooling fluid 240 intofirst pass 612. First pass 612 extends throughouter endwall 207 substantially parallel to trailingedge 312 andsecond pass 614. First pass 612 defines athird width 628 which, along withfirst width 624 andsecond width 626, may be selectively sized to enable a specific volumetric flow of cooling fluid 240 to flow therethrough such that a heat transfer coefficient of coolingfluid 240 is tuned to the specific heat transfer requirements ofouter endwall 207 and/orinner endwall 209. First pass 612 receives cooling fluid 240 fromfirst inlet portion 606 and second inlet portion 608 and channels cooling fluid 240 to turn 616. -
Turn 616 receives cooling fluid 240 fromfirst pass 612 and channels cooling fluid 240 tosecond pass 614. First pass 612,second pass 614, and turn 616 are oriented such thatfirst pass 612 channels cooling fluid 240 in afirst direction 630, andsecond pass 614 channels cooling fluid 240 in asecond direction 632 oppositefirst direction 630. Turn 616 changes a direction of flow of cooling fluid 240 fromfirst direction 630 tosecond direction 632. In the exemplary embodiment, turn 616 is a 180° turn such thatfirst direction 630 is diametrically oppositesecond direction 632. In alternative embodiments,first pass 612,second pass 614, and turn 616 may be oriented such thatfirst pass 612 andsecond pass 614 have any orientation that enablescore 300 to operate as described herein.Turn 616 receives cooling fluid 240 fromfirst pass 612, changes the direction of flow of cooling fluid 240, and channels cooling fluid 240 tosecond pass 614. -
Second pass 614 extends throughouter endwall 207 substantially parallel to trailingedge 312 and tofirst pass 612.Second pass 614 defines afourth width 634 which, along withfirst width 624,second width 626, andthird width 628, may be selectively sized to enable a specific volumetric flow of cooling fluid 240 such that a heat transfer coefficient of coolingfluid 240 is tuned to the specific heat transfer requirements ofouter endwall 207 and/orinner endwall 209.Second pass 614 receives cooling fluid 240 fromturn 616 and channels cooling fluid 240 tooutlets 618. - In the exemplary embodiment,
core 300 includes a singlefirst pass 612, a singlesecond pass 614, and asingle turn 616. In alternative embodiments,core 300 may include any number of passes and/or turns that enablescore 300 to operate as described herein. For example, in an alternative embodiment,core 300 may include three passes and two turns. In yet another alternative embodiment,core 300 may include four passes and three turns. -
Core 300 includes at least oneoutlet 618 downstream fromthroat 306. Whilecore 300 may include only asingle outlet 618, in the exemplary embodiment,core 300 includes a plurality ofoutlets 618 that channel cooling fluid fromcore 300 into hotgas flow path 232. For example,core 300 may include at least onefirst outlet 636 that extends fromfirst pass 612 throughouter endwall 207 and into hotgas flow path 232. In the exemplary embodiment,core 300 includes a plurality offirst outlets 636, each of which extends fromfirst pass 612 throughouter endwall 207 and into hotgas flow path 232. Cooling fluid 240 discharged into hotgas flow path 232 fromfirst outlets 636 may form a cooling film (not shown) onouter endwall 207 that protectsouter endwall 207. -
Core 300 may also include at least onesecond outlet 638 that extends fromsecond pass 614 throughouter endwall 207 and into hotgas flow path 232. In the exemplary embodiment,core 300 includes a plurality ofsecond outlets 638, each of which extends fromsecond pass 614 throughouter endwall 207 and into hotgas flow path 232. Cooling fluid 240 discharged into hotgas flow path 232 fromsecond outlets 638 may form a cooling film (not shown) onouter endwall 207 that facilitates protectingouter endwall 207. -
Core 300 may further include at least one third outlet 640 (shown inFIG. 4 ) that extends fromsecond pass 614 through trailingedge 312 ofinner endwall 209 and into hotgas flow path 232. In the exemplary embodiment,core 300 includes a plurality ofthird outlets 640, each of which extends fromsecond pass 614 through trailingedge 312 ofouter endwall 207 and into hotgas flow path 232. Cooling fluid 240 discharged into hotgas flow path 232 fromthird outlets 640 may form a cooling film (not shown) on trailingedge 312 ofouter endwall 207 that protects trailingedge 312 ofouter endwall 207. -
Core 300 may also include at least onefourth outlet 642 that extends fromturn 616 throughouter endwall 207 and into hotgas flow path 232. In the exemplary embodiment,core 300 includes a plurality offourth outlets 642, each of which extends fromturn 616 through trailingedge 312 ofouter endwall 207 and into hotgas flow path 232. Cooling fluid 240 discharged into hotgas flow path 232 fromfourth outlets 642 may form a cooling film (not shown) onouter endwall 207 that facilitates protectingouter endwall 207.Core 300 may includeoutlets 218 in any location that enablescore 300 to operate as described herein. - The size, shape, and relative position of first, second, third, and
fourth outlets fluid 240. For example,first outlets 636 may have a first size, andsecond outlets 638 may be sized with a second size that is smaller than the first size offirst outlets 636. As such,first outlets 636 form a cooling film (not shown) onouter endwall 207, andsecond outlets 638 supplement the cooling film withadditional cooling fluid 240. Additionally,more outlets passage 600 and facilitate reducing the pressure drop of cooling fluid 240 throughpassage 600. Accordingly, the size, shape, and position of first, second, third, andfourth outlets fluid 240. - In the exemplary embodiment,
first pass 612 andsecond pass 614 each include a plurality of turbulators orridges 644 that create turbulence withinfirst pass 612 andsecond pass 614. Specifically,turbulators 644 create turbulent flow within cooling fluid 240 to facilitate increasing the heat transfer coefficient of coolingfluid 240 withinfirst pass 612 andsecond pass 614. Increasing the heat transfer coefficient increases the overall heat transfer between cooling fluid 240 andouter endwall 207. In the exemplary embodiment,turbulators 644 have a height (not shown) that is about 10% that ofthird width 628 andfourth width 634. However,turbulators 644 may have any other height that enablescore 300 to operate as described herein. - In the exemplary embodiment,
core 300 includes a plurality of hollow core ties 646 that extend from eitherfirst inlet portion 606 to second inlet portion 608 orfirst pass 612 tosecond pass 614. Specifically,core 300 includes at least onefirst core tie 648 that extends fromfirst inlet portion 606 to second inlet portion 608 and at least onesecond core tie 650 extending fromfirst pass 612 tosecond pass 614. More specifically, in the exemplary embodiment,core 300 includes a singlefirst core tie 648 and a plurality of second core ties 650. First and second core ties 648 and 650, which define fluid passages therein, replenish downstream portions ofpassage 600 with coolingfluid 240. As coolingfluid 240 is channeled throughpassage 600, a temperature of cooling fluid 240 increases which facilitates decreasing the heat transfer coefficient of coolingfluid 240 and decreasing the overall heat transfer between cooling fluid 240 andouter endwall 207.Core ties 646 are “short cuts” that channel cooling fluid 240 from upstream portions ofpassage 600 to downstream portions ofpassage 600 without heat transfer between cooling fluid 240 andouter endwall 207. As such, cooling fluid 240 that is channeled throughcore ties 646 has a lower temperature than cooling fluid 240 that was channeled throughfirst pass 612,second pass 614, and turn 616. Accordingly,core ties 646 replenish downstream portions ofpassage 600 with cooling fluid 240 that has a lower temperature, which facilitates increasing the heat transfer coefficient of coolingfluid 240 and overall heat transfer between cooling fluid 240 andouter endwall 207. Core ties 646 may also be used as inspection ports to inspectcore 300. - During operation,
inlets coolant supply channel 233 and channel cooling fluid 240 tofirst inlet portion 606 and second inlet portion 608.First inlet portion 606 channels a portion of cooling fluid 240 throughfirst core tie 648 to replenish second inlet portion 608.First inlet portion 606 and second inlet portion 608 merge intofirst pass 612 and each channels cooling fluid 240 intofirst pass 612. First pass 612 channels a portion of cooling fluid 240 through second core ties 650 to replenishsecond pass 614 and channels another portion of cooling fluid 240 to turn 616. First pass 612 also channels a portion of cooling fluid throughfirst outlet 636 intohot gas path 232 to form a cooling film onouter endwall 207. Turn 616 channels a portion of cooling fluid 240 throughfourth outlet 642 intohot gas path 232 to form the cooling film onouter endwall 207 and channels the remainingcooling fluid 240 tosecond pass 614.Second pass 614 channels cooling fluid 240 through second andthird outlets edge 312. Coolingfluid 240 exchanges heat withouter endwall 207 as it is channeled throughpassage 600. As such, coolingfluid 240 facilitates coolingouter endwall 207 from withincore 300 and forms a protective cooling film that protectsouter endwall 207. - The serpentine configuration of
passage 600 enables cooling fluid 240 to cool a larger area ofouter endwall 207, thus increasing the overall heat transfer between cooling fluid 240 andouter endwall 207. Additionally, the serpentine orientation ofpassage 600 enables cooling fluid 240 to have a lower pressure that is approximately equal to the pressure ofcombustion gases 124 atthroat 306. Furthermore,widths passage 600 and to facilitate increasing the overall heat transfer between cooling fluid 240 andouter endwall 207. Moreover,outlets 618 channel cooling fluid 240 intohot gas path 232 to protectouter endwall 207 by forming a cooling film. Additionally,core ties 646 replenish downstream portions ofpassage 600 with coolingfluid 240. Accordingly, the arrangement ofcore 300 increases the overall heat transfer between cooling fluid 240 andouter endwall 207. - Although the discussion of
FIGS. 3 through 6 has describedcore 300 and its features in connection withouter endwall 207, it should be understood that thecore 300 may be employed with similar features ininner endwall 209 to achieve similar results and benefits. -
FIG. 7 is a flow diagram of anexemplary method 700 of cooling a component of a rotary machine. In the exemplary embodiment,method 700 includes inserting 702 a core into a plenum within the component. The core includes a passage including an inlet portion, at least one first pass, at least one second pass, at least one turn between respective first pass(es) and second pass(es). The inlet portion includes a divider that separates a first inlet portion from a second inlet portion, such that the inlet portion is a split pass inlet.Method 700 also includes channeling 704 a flow of cooling fluid into the first inlet portion and the second inlet portion.Method 700 further includes channeling 706 the flow of cooling fluid from the first inlet portion and the second inlet portion into the at least one first pass. The flow of cooling fluid from the first inlet portion merges with the flow of cooling fluid from the second inlet portion, and the at least one first pass channels the flow of cooling fluid in a first direction.Method 700 also includes channeling 708 the flow of cooling fluid from the at least one first pass into the at least one turn. The at least one turn changes a direction of flow of the cooling fluid from the first direction to a second direction opposite the first direction.Method 700 further includes channeling 710 the flow of cooling fluid from the at least one turn into the at least one second pass. The at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage is a serpentine passage. - The above described systems relate to a serpentine core for use in cooling portions of a hot gas path in a rotary machine. Specifically, in the exemplary embodiment, a rotary component includes an outer endwall formed in a nozzle of a turbine section within the rotary machine. The outer endwall includes a core for use in cooling the outer endwall. The core includes a serpentine passage including an inlet portion, a first pass, a second pass, and a turn between the first pass and the second pass. The inlet portion includes a divider that separates a first inlet portion from a second inlet portion, such that a split pass inlet is defined. The first pass, the second pass, and the turn include a plurality of outlets, each of which channels cooling fluid from the core into the hot gas path to form a cooling film on the outer endwall. A plurality of hollow core ties channels cooling fluid from an upstream portion of the core to a downstream portion of the core to enable the downstream portions to be replenished with lower temperature cooling fluid.
- In the exemplary embodiment, cooling fluid is channeled through the first pass, the second pass, and the turn to facilitate convective cooling of the outer endwall from within the core. The serpentine configuration of the first pass, the second pass, and the turn enables the cooling fluid to convectively cool a larger area of the outer endwall, thus increasing the overall heat transfer between the cooling fluid and the outer endwall. Additionally, the serpentine configuration enables the cooling fluid to circulate with a lower pressure that is substantially equal to the pressure of combustion gases at a throat of the nozzle. Furthermore, a width of each of the first pass, the second pass, and the turn is selected to facilitate modification of, or tune, the pressure drop of the cooling fluid through the first pass, the second pass, and the turn and to increase the overall heat transfer between the cooling fluid and the outer endwall. Moreover, the outlets channel cooling fluid into the hot gas path to facilitate forming a cooling film across the stator endwall. Additionally, the core ties replenish downstream portions of the core with cooling fluid. Thus, the core accomplishes both convective cooling of the endwall and film cooling of the endwall.
- Additionally, an exemplary technical effect of the systems and methods described herein includes at least one of: (a) removing heat from a rotary machine component; (b) increasing the heat transfer coefficient of a cooling fluid; (c) increasing the overall heat transfer between the cooling fluid and the rotary machine component; and (d) increasing rotary machine efficiency.
- Exemplary embodiments of systems and methods for cooling portions of a hot gas path of a rotary machine are described above in detail. The methods and systems 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 method may also be used in combination with other turbine components, and are not limited to practice only with the portions of the hot gas path of the rotary machine as described herein. Rather, the exemplary embodiment can be implemented and utilized in connection with many other rotary machine applications.
- 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 (20)
1. A core for use in cooling a component used in a rotary machine, said core comprising:
a passage comprising:
a first inlet portion;
a second inlet portion;
a divider separating said first inlet portion from said second inlet portion such that said first inlet portion, said second inlet portion, and said divider define a split pass inlet;
at least one first pass for channeling a flow of cooling fluid in a first direction from the split pass inlet;
at least one second pass for channeling the flow of cooling fluid in a second direction substantially opposite the first direction;
at least one turn for changing a direction of flow of the cooling fluid from the first direction to the second direction, wherein said at least one first pass, said at least one second pass, and said at least one turn are arranged such that said passage defines a serpentine passage; and
an outlet extending from said at least one first pass to an exterior surface of said core and oriented to channel a flow of cooling fluid from said at least one first pass, through said outlet, to the exterior surface of said core to form a protective film on the exterior surface of said core.
2. The core of claim 1 , wherein said passage comprises at least one first inlet for channeling the flow of cooling fluid into said first inlet portion and at least one second inlet for channeling the flow of cooling fluid into said second inlet portion.
3. The core of claim 1 , wherein said at least one first pass and said at least one second pass each comprise a plurality of turbulators for generating turbulence within the flow of cooling fluid.
4. The core of claim 1 , wherein said passage further comprises a plurality of core ties for channeling a portion of the flow of cooling fluid from an upstream portion of said passage to a downstream portion of said passage.
5. The core of claim 4 , wherein said plurality of core ties comprises at least one first core tie for channeling a portion of the flow of cooling fluid from said first inlet portion to said second inlet portion.
6. The core of claim 4 , wherein said plurality of core ties comprises at least one second core tie for channeling a portion of the flow of cooling fluid from said at least one first pass to said at least one second pass.
7. A gas turbine system comprising:
a turbine section coupled in flow communication with a combustion system, wherein said turbine section comprises:
an inner endwall circumscribing the longitudinal axis of the gas turbine system;
an outer endwall circumscribing a longitudinal axis of the gas turbine system and said inner endwall;
a plurality of airfoils extending between said outer endwall and said inner endwall; and
a core positioned within at least one of said outer endwall and said inner endwall for cooling at least one of said outer endwall and said inner endwall, said core comprising:
a passage comprising:
a first inlet portion;
a second inlet portion;
a divider separating said first inlet portion from said second inlet portion such that said first inlet portion, said second inlet portion, and said divider define a split pass inlet;
at least one first pass for channeling a flow of cooling fluid in a first direction from the split pass inlet;
at least one second pass for channeling a flow of cooling fluid in a second direction substantially opposite the first direction; and
at least one turn for changing a direction of flow of the cooling fluid from the first direction to the second direction, wherein said at least one first pass, said at least one second pass, and said at least one turn are arranged such that said passage defines a serpentine passage, wherein said passage further comprises a plurality of outlets extending through said outer endwall, wherein said plurality of outlets comprises at least one first outlet extending from said at least one first pass through said outer endwall, and wherein a portion of the flow of cooling fluid is channeled through said at least one first outlet to form a protective film on said outer endwall.
8. The gas turbine system of claim 7 , said passage comprises a first inlet for channeling the flow of cooling fluid into said first inlet portion and a second inlet for channeling the flow of cooling fluid into said second inlet portion.
9. The gas turbine system of claim 7 , wherein adjacent airfoils of said plurality of airfoils define a throat therebetween, and wherein said passage further comprises an upstream portion and a downstream portion, and wherein said upstream portion is positioned upstream of said throat and said downstream portion is positioned downstream of said throat.
10. (canceled)
11. (canceled)
12. The gas turbine system of claim 7 , wherein said plurality of outlets comprises at least one second outlet extending from said at least one second pass through said outer endwall, and wherein a portion of the flow of cooling fluid is channeled through said at least one second outlet to form a protective film on said outer endwall.
13. The gas turbine system of claim 7 , wherein said outer endwall comprises a trailing edge and said plurality of outlets comprises at least one third outlet extending from said at least one second pass through said trailing edge, and wherein a portion of the flow of cooling fluid is channeled through said at least one third outlet to form a protective film on said trailing edge.
14. The gas turbine system of claim 7 , wherein said plurality of outlets comprises at least one fourth outlet extending from said at least one turn through said outer endwall, and wherein a portion of the flow of cooling fluid is channeled through said at least one fourth outlet to form a protective film on said outer endwall.
15. A method of cooling a component of a rotary machine, said method comprising:
inserting a core into a plenum within the component, the core including a passage including an inlet portion, at least one first pass, at least one outlet extending from the at least one first pass to an exterior surface of the core, at least one second pass, at least one turn, the inlet portion including a first inlet portion, a second inlet portion, and a divider, wherein the divider separates the first inlet portion from the second inlet portion such that the inlet portion is a split pass inlet;
channeling a flow of cooling fluid into the first inlet portion and the second inlet portion;
channeling the flow of cooling fluid from the first inlet portion and the second inlet portion into the at least one first pass, wherein the flow of cooling fluid from the first inlet portion merges with the flow of cooling fluid from the second inlet portion, and wherein the at least one first pass channels the flow of cooling fluid in a first direction;
channeling a first portion of the flow of cooling fluid from the at least one first pass through the outlet and to the exterior surface of the core to form a protective film on the exterior surface of the core;
channeling a second portion of the flow of cooling fluid from the at least one first pass into the at least one turn, wherein the at least one turn changes a direction of flow of the cooling fluid from the first direction to a second direction opposite the first direction; and
channeling the second portion of the flow of cooling fluid from the at least one turn into the at least one second pass, wherein the at least one first pass, the at least one second pass, and the at least one turn are arranged such that the passage defines a serpentine passage.
16. The method of claim 15 , further comprising channeling the flow of cooling fluid into a first inlet and a second inlet.
17. The method of claim 15 , further comprising channeling the flow of cooling fluid from the first inlet portion to the second inlet portion through at least one first core tie.
18. The method of claim 15 , further comprising channeling the flow of cooling fluid from the at least one first pass to the at least one second pass through at least one second core tie.
19. The method of claim 15 , further comprising generating turbulence within the flow of cooling fluid using a plurality of turbulators.
20. The method of claim 15 , further comprising replenishing the flow of cooling fluid in the at least one second pass by bypassing at least one turn by channeling the flow of cooling fluid from the first inlet portion to the second inlet portion through at least one first core tie.
Priority Applications (4)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US16/875,604 US11174788B1 (en) | 2020-05-15 | 2020-05-15 | Systems and methods for cooling an endwall in a rotary machine |
CN202110410714.XA CN113669119A (en) | 2020-05-15 | 2021-04-14 | System and method for cooling endwalls in rotary machines |
JP2021070710A JP2021179208A (en) | 2020-05-15 | 2021-04-19 | Systems and methods for cooling endwall in rotary machine |
EP21170808.6A EP3916200A1 (en) | 2020-05-15 | 2021-04-27 | Systems and methods for cooling an endwall in a rotary machine |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US16/875,604 US11174788B1 (en) | 2020-05-15 | 2020-05-15 | Systems and methods for cooling an endwall in a rotary machine |
Publications (2)
Publication Number | Publication Date |
---|---|
US11174788B1 US11174788B1 (en) | 2021-11-16 |
US20210355879A1 true US20210355879A1 (en) | 2021-11-18 |
Family
ID=75728634
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US16/875,604 Active US11174788B1 (en) | 2020-05-15 | 2020-05-15 | Systems and methods for cooling an endwall in a rotary machine |
Country Status (4)
Country | Link |
---|---|
US (1) | US11174788B1 (en) |
EP (1) | EP3916200A1 (en) |
JP (1) | JP2021179208A (en) |
CN (1) | CN113669119A (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4273366A1 (en) * | 2022-05-02 | 2023-11-08 | Siemens Energy Global GmbH & Co. KG | Turbine component having platform cooling circuit |
Citations (16)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5545002A (en) * | 1984-11-29 | 1996-08-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Stator vane mounting platform |
US6254333B1 (en) * | 1999-08-02 | 2001-07-03 | United Technologies Corporation | Method for forming a cooling passage and for cooling a turbine section of a rotary machine |
US6905302B2 (en) * | 2003-09-17 | 2005-06-14 | General Electric Company | Network cooled coated wall |
US8011881B1 (en) * | 2008-01-21 | 2011-09-06 | Florida Turbine Technologies, Inc. | Turbine vane with serpentine cooling |
US20120034102A1 (en) * | 2010-08-09 | 2012-02-09 | General Electric Company | Bucket assembly cooling apparatus and method for forming the bucket assembly |
US20130230394A1 (en) * | 2012-03-01 | 2013-09-05 | General Electric Company | Turbine Bucket with Pressure Side Cooling |
US20140072400A1 (en) * | 2012-09-10 | 2014-03-13 | General Electric Company | Serpentine Cooling of Nozzle Endwall |
US8794921B2 (en) * | 2010-09-30 | 2014-08-05 | General Electric Company | Apparatus and methods for cooling platform regions of turbine rotor blades |
US8814518B2 (en) * | 2010-10-29 | 2014-08-26 | General Electric Company | Apparatus and methods for cooling platform regions of turbine rotor blades |
US8905714B2 (en) * | 2011-12-30 | 2014-12-09 | General Electric Company | Turbine rotor blade platform cooling |
US9021816B2 (en) * | 2012-07-02 | 2015-05-05 | United Technologies Corporation | Gas turbine engine turbine vane platform core |
US9222364B2 (en) * | 2012-08-15 | 2015-12-29 | United Technologies Corporation | Platform cooling circuit for a gas turbine engine component |
US9416665B2 (en) * | 2012-02-15 | 2016-08-16 | United Technologies Corporation | Cooling hole with enhanced flow attachment |
US9518468B2 (en) * | 2011-02-17 | 2016-12-13 | Rolls-Royce Plc | Cooled component for the turbine of a gas turbine engine |
US9856747B2 (en) * | 2010-07-15 | 2018-01-02 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
US20180355726A1 (en) * | 2017-06-13 | 2018-12-13 | General Electric Company | Platform cooling arrangement in a turbine rotor blade |
Family Cites Families (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US6170264B1 (en) | 1997-09-22 | 2001-01-09 | Clean Energy Systems, Inc. | Hydrocarbon combustion power generation system with CO2 sequestration |
US7686581B2 (en) * | 2006-06-07 | 2010-03-30 | General Electric Company | Serpentine cooling circuit and method for cooling tip shroud |
JP2009128509A (en) | 2007-11-21 | 2009-06-11 | Nitto Denko Corp | Liquid crystal display device |
CN101307915B (en) | 2008-06-24 | 2010-06-02 | 北京航空航天大学 | Gas turbine preevaporation combustion-chamber for combusting ethanol fuel |
CN101435585B (en) | 2008-11-28 | 2010-10-13 | 北京大学 | Gas turbine combined type fuel evaporating and atomizing combustion apparatus |
US9926799B2 (en) * | 2015-10-12 | 2018-03-27 | United Technologies Corporation | Gas turbine engine components, blade outer air seal assemblies, and blade outer air seal segments thereof |
-
2020
- 2020-05-15 US US16/875,604 patent/US11174788B1/en active Active
-
2021
- 2021-04-14 CN CN202110410714.XA patent/CN113669119A/en active Pending
- 2021-04-19 JP JP2021070710A patent/JP2021179208A/en active Pending
- 2021-04-27 EP EP21170808.6A patent/EP3916200A1/en active Pending
Patent Citations (18)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5545002A (en) * | 1984-11-29 | 1996-08-13 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation S.N.E.C.M.A. | Stator vane mounting platform |
US6254333B1 (en) * | 1999-08-02 | 2001-07-03 | United Technologies Corporation | Method for forming a cooling passage and for cooling a turbine section of a rotary machine |
US6905302B2 (en) * | 2003-09-17 | 2005-06-14 | General Electric Company | Network cooled coated wall |
US8011881B1 (en) * | 2008-01-21 | 2011-09-06 | Florida Turbine Technologies, Inc. | Turbine vane with serpentine cooling |
US9856747B2 (en) * | 2010-07-15 | 2018-01-02 | Siemens Aktiengesellschaft | Nozzle guide vane with cooled platform for a gas turbine |
US20120034102A1 (en) * | 2010-08-09 | 2012-02-09 | General Electric Company | Bucket assembly cooling apparatus and method for forming the bucket assembly |
US8794921B2 (en) * | 2010-09-30 | 2014-08-05 | General Electric Company | Apparatus and methods for cooling platform regions of turbine rotor blades |
US8814518B2 (en) * | 2010-10-29 | 2014-08-26 | General Electric Company | Apparatus and methods for cooling platform regions of turbine rotor blades |
US9518468B2 (en) * | 2011-02-17 | 2016-12-13 | Rolls-Royce Plc | Cooled component for the turbine of a gas turbine engine |
US8905714B2 (en) * | 2011-12-30 | 2014-12-09 | General Electric Company | Turbine rotor blade platform cooling |
US9416665B2 (en) * | 2012-02-15 | 2016-08-16 | United Technologies Corporation | Cooling hole with enhanced flow attachment |
US9109454B2 (en) * | 2012-03-01 | 2015-08-18 | General Electric Company | Turbine bucket with pressure side cooling |
US20130230394A1 (en) * | 2012-03-01 | 2013-09-05 | General Electric Company | Turbine Bucket with Pressure Side Cooling |
US9021816B2 (en) * | 2012-07-02 | 2015-05-05 | United Technologies Corporation | Gas turbine engine turbine vane platform core |
US9222364B2 (en) * | 2012-08-15 | 2015-12-29 | United Technologies Corporation | Platform cooling circuit for a gas turbine engine component |
US20140072400A1 (en) * | 2012-09-10 | 2014-03-13 | General Electric Company | Serpentine Cooling of Nozzle Endwall |
US20180355726A1 (en) * | 2017-06-13 | 2018-12-13 | General Electric Company | Platform cooling arrangement in a turbine rotor blade |
US10323520B2 (en) * | 2017-06-13 | 2019-06-18 | General Electric Company | Platform cooling arrangement in a turbine rotor blade |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP4273366A1 (en) * | 2022-05-02 | 2023-11-08 | Siemens Energy Global GmbH & Co. KG | Turbine component having platform cooling circuit |
Also Published As
Publication number | Publication date |
---|---|
CN113669119A (en) | 2021-11-19 |
US11174788B1 (en) | 2021-11-16 |
JP2021179208A (en) | 2021-11-18 |
EP3916200A1 (en) | 2021-12-01 |
Similar Documents
Publication | Publication Date | Title |
---|---|---|
US11655718B2 (en) | Blade with tip rail, cooling | |
US10830051B2 (en) | Engine component with film cooling | |
US10577944B2 (en) | Engine component with hollow turbulators | |
US10753207B2 (en) | Airfoil with tip rail cooling | |
US10443397B2 (en) | Impingement system for an airfoil | |
US20170107827A1 (en) | Turbine blade | |
US10830060B2 (en) | Engine component with flow enhancer | |
US10830057B2 (en) | Airfoil with tip rail cooling | |
US10563518B2 (en) | Gas turbine engine trailing edge ejection holes | |
US10718217B2 (en) | Engine component with cooling passages | |
US10408062B2 (en) | Impingement system for an airfoil | |
US10436048B2 (en) | Systems for removing heat from turbine components | |
EP3916200A1 (en) | Systems and methods for cooling an endwall in a rotary machine | |
US10808547B2 (en) | Turbine engine airfoil with cooling | |
US10711620B1 (en) | Insert system for an airfoil and method of installing same | |
US20180156041A1 (en) | Engine with chevron pin bank | |
US9376918B2 (en) | Aerofoil cooling arrangement | |
US10612389B2 (en) | Engine component with porous section | |
US10900362B2 (en) | Insert system for an airfoil and method of installing same | |
US20230417150A1 (en) | Augmented cooling for tip clearance optimization | |
US10364685B2 (en) | Impingement system for an airfoil |
Legal Events
Date | Code | Title | Description |
---|---|---|---|
FEPP | Fee payment procedure |
Free format text: ENTITY STATUS SET TO UNDISCOUNTED (ORIGINAL EVENT CODE: BIG.); ENTITY STATUS OF PATENT OWNER: LARGE ENTITY |
|
STCF | Information on status: patent grant |
Free format text: PATENTED CASE |
|
AS | Assignment |
Owner name: GE INFRASTRUCTURE TECHNOLOGY LLC, SOUTH CAROLINA Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:GENERAL ELECTRIC COMPANY;REEL/FRAME:065727/0001 Effective date: 20231110 |