US20100054915A1 - Airfoil insert - Google Patents
Airfoil insert Download PDFInfo
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- US20100054915A1 US20100054915A1 US12/200,160 US20016008A US2010054915A1 US 20100054915 A1 US20100054915 A1 US 20100054915A1 US 20016008 A US20016008 A US 20016008A US 2010054915 A1 US2010054915 A1 US 2010054915A1
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- Prior art keywords
- insert
- airfoil
- flow
- wall
- insert wall
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- 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
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
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- 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
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- 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
Abstract
An airfoil insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior extending inside the insert wall from a first end to second end, and an exterior extending outside the insert wall from the first end to the second end. The contact element is formed on the exterior of the insert wall. The flow director is formed on the insert wall at a boundary between the interior and the exterior. The flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall.
Description
- The subject matter of this application relates generally to gas turbine engines, and specifically to cooling techniques for the airfoil sections of turbine blades and vanes. In particular, the invention concerns an insert for convective cooling the interior surfaces of turbine airfoils exposed to high-temperature working fluid flow.
- Gas turbine engines are built around a power core comprising a compressor, a combustor and a turbine, which are arranged in flow series with a forward (upstream) inlet and an aft (downstream) exhaust. The compressor compresses air from the inlet, which is mixed with fuel in the combustor and ignited to produce hot combustion gases. The hot combustion gases drive the turbine section, and are exhausted with the downstream flow.
- The turbine drives the compressor via a shaft or a series of coaxially nested shaft spools, each driven at different pressures and speeds. The spools employ a number of stages comprised of alternating rotor blades and stator vanes. The vanes and blades typically have airfoil cross sections, in order to facilitate compression of the incoming air and extraction of rotational energy in the turbine.
- In addition to its use as an oxidant, compressor air is also utilized to cool downstream engine components, particular turbine and exhaust parts exposed to hot gas flow. Depending upon application, compressed air is also utilized for environmental control, pneumatics and other accessory functions.
- Energy not used to drive the compressor and provide cooling or accessory functions is available for external use. In ground-based industrial gas turbines, for example, power is typically provided in the form of rotational energy, which is used to drive an electrical generator or other mechanical load. In aviation applications, on the other hand, reactive thrust is generated directly from the exhaust.
- In turbofan engines, one of the spools also drives a forward fan or ducted propeller, producing additional thrust from bypass flow directed around the engine core. Turbofans are either directly driven by the low-pressure turbine spool, or employ a reduction gearbox to slow the fan, reducing noise and increasing efficiency.
- The majority of commercial aircraft employ high-bypass turbofan engines, which generate most of their thrust from bypass flow. Supersonic jets and other high-performance aircraft typically employ low-bypass turbofans, which rely primarily on reactive thrust from the exhaust. Low-bypass turbofans are louder and less fuel efficient, but provide greater response and specific thrust. Low-bypass turbofans are also commonly configured for afterburning, in which additional fuel is injected into in an augmentor assembly downstream of the turbine, where it is ignited to provide additional thrust.
- The main goals in gas turbine engine design are efficiency, performance and reliability. Efficiency and performance both favor high combustion temperatures, which increase the engine's thermodynamic efficiency, specific thrust, and maximum power output. Unfortunately, high combustion temperatures also increase thermal and mechanical loads, particularly on turbine airfoils downstream of the combustor. This reduces service life and reliability, and increases operational costs associated with maintenance and repairs.
- There is thus a need for enhanced turbine airfoil cooling techniques. In particular, there is a need for techniques that not only improve cooling efficiency, reducing the required cooling fluid mass flow rate and resulting energy losses, but also improve cooling efficacy, reducing thermal stresses, extending service life and increasing reliability.
- This disclosure concerns an airfoil insert for convective cooling and a method of cooling using the insert. The insert comprises an insert wall, a contact element and a flow director. The insert wall defines an interior region extending inside the insert from a first end to a generally opposed second end, and an exterior region extending along the outside of the insert from the first end to the second end.
- The contact element is formed on the exterior of the insert wall between the first end and the second end, for attaching the insert to an airfoil and for spacing the insert wall from the internal airfoil surfaces. The flow director is formed on the insert wall at a boundary between the exterior and interior, and increases the heat transfer coefficient of convective flow along the insert by directing the convective flow to the exterior region, between the insert wall and the surface of the cooling passage.
- The method comprises positioning the insert along an internal surface of an airfoil, spacing the insert from the internal surface, and restricting convective flow along the insert to a region between the insert and the inner surface. This increases the Reynolds number of the convective flow, which in turn increases the heat transfer coefficient.
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FIG. 1 is a cross-sectional schematic of an airfoil insert and airfoil. -
FIG. 2A is a top schematic view of an airfoil section and insert, in embodiment with a collar and an inlet for internal flow. -
FIG. 2B is a top schematic view of an airfoil section and insert, in an embodiment with spacing tabs and an upstream flow stop. -
FIG. 3A is a top schematic view of an airfoil section and insert, in an embodiment with spacing ribs and an upstream flow stop. -
FIG. 3B is top schematic view of an airfoil section and insert, in an embodiment with spacing ribs and multiple inlets for internal flow. -
FIG. 4A is a perspective view of an airfoil insert with indirect convective flow apertures and a downstream outlet. -
FIG. 4B is a perspective view of an airfoil insert with supplemental convective flow apertures and a downstream flow stop. -
FIG. 5A is a top schematic view of a U-shaped (open-geometry) insert and airfoil section. -
FIG. 5B is a perspective view of the insert inFIG. 5A . -
FIG. 6A is a top schematic view of a two-panel (open-geometry) insert and airfoil section. -
FIG. 6B is a perspective view of the insert inFIG. 6A . -
FIG. 1 is a cross-sectional schematic ofinsert 10 forairfoil 20.Insert 10 comprisesinsert wall 11 withfirst end 12,second end 13 andcontact element 14 for attachinginsert 10 toairfoil 20 and for positioninginsert wall 11 withinairfoil section 21. Insert 10 increases the heat transfer coefficient of convective flow by directing the convective flow aroundinsert wall 11, away frominternal region 15 and intoexternal region 16, betweeninsert wall 11 andairfoil section 21. - Airfoil 20 comprises
airfoil section 21,inner platform 22 andouter platform 23.Airfoil section 21 extends axially between leadingedge 24 andtrailing edge 25, and radially betweenplatforms Internal cooling passages internal surfaces 27 ofairfoil section 21. Augmentors such as trip strips 28 and pedestals 29 are formed alonginternal surfaces 27 ofpassages airfoil section 21 that are exposed to hot working fluid flow. - In the particular embodiment of
FIG. 1 ,airfoil 20 is a stationary turbine vane for use in a turbojet or turbofan engine. In this embodiment,airfoil 20 is typically attached to a turbine case or flow duct atinner platform 22 andouter platform 23, using mechanical coupling structures such as hooks or by formingplatforms 23 as part of a case or shroud assembly. In other embodiments,airfoil 20 is configured for use in an industrial gas turbine engine, andplatforms - Alternatively,
airfoil 20 is formed as a rotating blade. In these embodiments,airfoil section 21 is typically formed into a tip atouter platform 23, andinner platform 22 accommodates a root structure or other means of attachment to a rotating shaft. In further embodiments,airfoil 20 is provided with additional structures for improved working fluid flow control, including, but not limited to, platform seals, knife edge seals, tip caps and squealer tips. -
Airfoil 20 is exposed to a generally axial flow of combustion gas F, which flows acrossairfoil section 21 from leadingedge 24 to trailingedge 25. Flow F has a radially inner flow margin atinner platform 22, and a radially outer flow margin atouter platform 23, or, in blade embodiments, at the blade tip. - To protect
airfoil 20 from wear and tear due to the working fluid flow, its various components are manufactured from durable, heat-resistant materials such as high-temperature alloys and superalloys. Typically, surfaces that are directly exposed to hot gas are also coated with a protective coating such as a ceramic thermal barrier coating (TBC), an aluminide coating, a metal oxide coating, a metal alloy coating, a superalloy coating, or a combination thereof. -
Airfoil 20 is manufactured as a hollow structure withinternal cooling passages internal surfaces 27, forming channels or conduits for cooling fluid flow throughairfoil section 21. In turbofan embodiments, the cooling fluid is usually provided from a compressed air source such as compressor bleed air. In ground-based industrial gas turbine embodiments, other fluids such as steam are also used. - The flow of cooling fluid depends upon the particular configuration of
airfoil 20. In the embodiment ofFIG. 1 , for example, cooling flow C is radially inward through leadingedge cooling passage 26A (in the direction fromouter platform 23 toward inner platform 22), and exits coolingpassage 26A in downstream cooling flow direction D. Inserpentine passages - As shown in
FIG. 1 , trip strips (or turbulators) 28 are provided to improve cooling alonginternal passage 26A, and pedestals (or pins) 29 are provided to improve cooling alonginternal passages internal cooling passages insert 10. -
Airfoil 20 also employs external cooling, in which additional cooling fluid is directed from cold internal surface(s) 27 to the hot (outer) surfaces ofairfoil section 21. The cooling fluid is directed through a combination of film cooling hole structures, including, but not limited to, “showerhead”openings 30A in coolingpassage 26A along leadingedge 24, film cooling holes 30B inpassage 26D, andfilm cooling slots 30C along trailingedge 25. - Like
airfoil 20, insert 10 is manufactured from a durable, heat-resistant material such as a metal alloy or superalloy. In typical embodiments, insert 10 is not provided with a TBC coating becauseinsert wall 11 is not directly exposed to hot combustion gas flow. In other embodiments, an anti-oxidant coating or other protective coating is applied. In further embodiments, insert 10 is provided with a flame spray coating or other coating for forming a fluid seal, a contact surface, a coupling or a mechanical attachment betweeninsert wall 11 andairfoil section 21. - As shown in
FIG. 1 , insert 10 is positioned along coolingpassage 26A in a downstream cooling flow direction, such thatfirst end 12 is an upstream end andsecond end 13 is a downstream end. In other configurations the flow is reversed, or insert 10 is inserted frominner platform 22 rather thanouter platform 23, such that the upstream and downstream ends are interchanged. -
Insert wall 11 definesinternal region 15, extending along the inside (interior) ofinsert 10 betweenfirst end 12 andsecond end 13, andexternal region 16, extending along the outside (exterior) ofinsert 10 betweenfirst end 12 andsecond end 13.External region 16 also extends along coolingpassage 26A, betweeninsert wall 11 andinternal surface 27 ofairfoil section 21. - In some embodiments, insert
wall 11 has a closed-tube geometry in whichinterior 15 andexterior 16 are defined along a substantially complete cross-sectional perimeter (see, e.g.,FIGS. 2A-4B ). Alternatively, insertwall 11 has a U-shaped, C-shaped, two-panel or other open-tube geometry, in whichinterior region 15 is bounded on at least one side by internal surfaces 27 (that is, the inner or interior surfaces of the cooling passages insideairfoil section 21; see, e.g.,FIGS. 5A-6B ). - The particular form of
contact element 14 varies. In the closed-geometry embodiment ofFIG. 1 , for example,contact element 14 comprises a collar formed onto the upstream end ofinsert wall 11, for attachinginsert 10 toairfoil 20 and for spacinginsert wall 11 frominternal surfaces 27 of coolingpassage 26A.Insert 10 also provides convective flow apertures (see below) that direct convective flow alongexterior region 16, and an inlet to maintain a positive overpressure for non-convective flow throughinternal region 15, in order to generate downstream cooling fluid flow D atsecond end 13. -
Insert 10 increases the heat transfer coefficient withinairfoil 20 by directing flow aroundinsert wall 11, excluding convective flow frominternal region 15 and restricting it toexternal region 16. Essentially, the heat transfer coefficient varies with the Reynolds number, which describes the ratio of inertial to viscous forces (inertial and viscous effects) in the flow. When convective flow is restricted toexternal region 16, the flow area is reduced and the impedance rises. The convective flow becomes less laminar and more turbulent, increasing the Reynolds number. This enhances flow interactions alonginternal surfaces 27 of coolingpassage 26A, allowing greater thermal transfer fromairfoil section 21. - In some embodiments, convective flow is also described in terms of Mach number. In these embodiments, insert 10 produces Mach acceleration in the convective flow, increasing the heat transfer coefficient by generating greater turbulence and other flow interactions in the region between
insert wall 11 and internal airfoil surfaces 27. - Increasing the heat transfer coefficient enhances convective cooling within
airfoil section 21. In particular, insert 10 lowers operating temperatures and thermal gradients, reducing thermal stresses and increasing service life.Insert 10 also reduces the cooling flow required to achieve these benefits, improving cooling efficiency and reserving capacity for additional downstream cooling loads. -
FIG. 2A is a top schematic view ofairfoil section 21 andinsert 10, located inmidbody cooling channel 26B (shown in hidden lines). In this embodiment, insert 10 comprisescontact element 14 withcollar 31 andinlet 32 for directing flow to the interior ofinsert wall 11. -
Airfoil section 21 extends axially between leadingedge 24 and trailingedge 25, along pressure or concave side 33 (the upper surface inFIG. 2A ) and suction or convex side 34 (the lower surface).Internal cooling passages 26A-26D are defined along internal airfoil surfaces 27, and extend in a generally radial sense along airfoil section 21 (that is, into the plane of the figure). - As shown in
FIG. 2A , leadingedge cooling passage 26A and firstmidbody cooling passage 26B exhibit open-ended designs, and each is configured to accept particular embodiments of insert 10 (see, e.g.,FIG. 2B , below). Secondmidbody cooling passage 26C and trailingedge cooling body 26D exhibit closed-end geometries (shown in dashed or hidden lines), and are not configured forinsert 10. In alternate embodiments, different combinations ofcooling passages insert 10. - In this particular embodiment,
Insert 10 is located in firstmidbody cooling passage 26B.Collar 31 provides means for positioninginsert 10 withincooling passage 26B, such thatcollar 31 extends outside of coolingpassage 26B and insertwall 11 is spaced within coolingpassage 26B.Internal surface 27 defines the outside edge of coolingpassage 26B, which is located between the outside edge of insert 11 (inside the cooling passage) and the outside edge of collar 31 (outside the cooling passage). -
Collar 31 also provides means for attachinginsert 10 toairfoil section 21, for example by welding or brazing, by thermal or friction fitting, or by forming a mechanical attachment via a flame spray coating or other material applied to insertwall 11 or tointernal surface 27 of coolingpassage 26B. In some embodiments, the attachment features are constructed such thatinsert 10 is removable for adjustment and repair. In other embodiments, insert 10 is permanently attached toairfoil 21. In these embodiments, insert 10 also functions as a cast-in wall within coolingpassage 26B, without requiring the same complex manufacturing steps. - In the particular embodiment of
FIG. 2A ,collar 31 is formed on the exterior ofinsert 10 at the upstream end (or first end) ofinsert wall 11, and extends beyond the cross-sectional area of coolingpassage 26B. In other embodiments,collar 31 is formed within the cross-sectional area of coolingpassage 26B, and is located anywhere between the first and second ends ofinsert 10. In further embodiments, a number ofcollars 31 or other spacing and attachment means are provided at various locations alonginsert wall 11. -
Inlet 32 is typically formed by stamping, drilling, cutting or machining an opening or orifice on the upstream end ofinsert wall 11.Inlet 32 defines a boundary between the interior and exterior ofinsert wall 11, and directs flow through this boundary intoinsert 10. The internal flow is provided with a positive overpressure, as compared to the exterior flow, and is utilized for downstream cooling functions. In some embodiments, for example, the internal flow is converted to convective flow via a number of indirect (downstream) apertures ininsert wall 11, and in other embodiments the internal flow conducted through an outlet to a downstream cooling load (seeFIGS. 4A and 4B ). -
FIG. 2B is top schematic view ofairfoil section 21 andinsert 10, located in leadingedge cooling channel 26A. In this embodiment, insert 10 comprisescontact element 14 withspacing tabs 35 and flow stop 36, for directing flow to the exterior ofinsert wall 11 via direct-flow convection apertures 37. - Spacing
tabs 35 comprise spacing and contact or coupling members formed onto the exterior ofinsert wall 11 via techniques such as stamping, welding, brazing, milling, molding, cutting and machining, as described above forcollar 31 ofFIG. 2A . Similarly, spacingtabs 35 provide means to position insert 10 withincooling channel 26A, spacinginsert wall 11 frominternal surfaces 27 ofairfoil section 21, and means for attachinginsert 10 toairfoil section 21, within coolingpassage 26A. - In some embodiments, spacing tabs (or fingers) 35 extend within the cross-sectional area of cooling
passage 26A, and are provided anywhere along the length ofinsert 10 between the upstream and downstream ends ofinsert wall 11. Alternatively, spacingtabs 35 are provided at the first (upstream) end ofinsert wall 11, and sometimes extend beyond the cross-sectional area of coolingpassage 26A, as described above forcollar 31 ofFIG. 2A . - Direct-
flow convection apertures 37 are sometimes co-formed withcontact element 14, for example by defining the apertures betweentabs 35.Apertures 37 direct cooling fluid flow aroundinsert 10, into the convective flow region betweeninsert wall 11 and internal surface(s) 27 ofairfoil section 21. - In some embodiments, spacing
tabs 35 are adjustable by bending, twisting, turning or similar mechanical manipulation, in order to change the spacing betweeninsert wall 11 andcooling passage 26A, or to change the dimensions ofapertures 37. This allows the convective flow rate and heat transfer coefficient to be adjusted to suit the particular cooling needs ofairfoil section 21. -
FIG. 3A is top schematic view ofairfoil section 21 andinsert 10, located in leadingedge cooling channel 26A. In this embodiment insert 10 contacts the interior airfoil surface along spacingribs 38, and flowstop 36 directs flow to the exterior ofinsert wall 11 via direct-flow convection apertures 37. - Spacing
ribs 38 comprise spacing and attachment members formed by casting, welding, brazing, milling, molding, cutting or machininginternal cooling passage 26A. Spacingribs 38 provide means for spacinginsert wall 11 from internal surface(s) 27 of coolingpassage 26A, and for attachingairfoil section 21 to insert 10 alongcontact element 14. - As shown in
FIG. 3A , onespacing rib 38 is provided along coolingpassage 26A oppositepressure surface 33 ofairfoil section 21, and anotherrib 38 is provided oppositesuction surface 34. In alternate embodiments, one, two, three ormore ribs 38 are located opposite any ofpressure surface 33,suction surface 34, leadingedge surface 24 or trailingedge surface 25. In further embodiments, pin-fins and other stand-off features are utilized instead of fibs, where these features have various different cross-sectional geometries. -
Flow stop 36 comprises a plug, wall, baffle, flow block or other structure formed acrossinsert wall 11, using any of the mechanical fabrication techniques described above. As shown inFIG. 3A , stop 36 is an upstream flow stop, formed onto the upstream end ofinsert wall 11 at the boundary between the internal and external regions ofinsert 10. In other embodiments, flow stop 36 is a downstream stop, formed onto the downstream end ofinsert 10, or an intermediate stop, formed anywhere along insert wall 11 (see, e.g.,FIGS. 6A and 6B ). - Flow stop 36 blocks flow to the interior of
insert wall 11, stopping the internal flow throughinsert 10. Convective flow is directed throughapertures 37 to the exterior ofinsert 10, to the convective region along coolingpassage 26A, betweeninsert wall 11 andinternal surfaces 27 ofairfoil section 21. -
FIG. 3B is a top schematic view ofairfoil section 21 andinsert 10, located in leadingedge cooling channel 26A.Insert 10 contacts the inner airfoil surface alongribs 38, as shown inFIG. 3A , above, and directs convective flow throughapertures 37. In this embodiment, however, insert 10 also provides internal flow viamultiple inlets 32. -
FIGS. 2A , 2B, 3A and 3B illustrate a range of representative embodiments in which the various contact, coupling, attachment, spacing and flow direction elements take on a variety of different forms. The numbers, sizes and shapes of individual collar, inlet, aperture, tab, inlet, stop and rib elements also vary, in order to generate a desired ratio of convective (exterior) and non-convective (internal) flow, and to regulate these flows in a desired manner around the exterior and interior ofinsert wall 11. In some embodiments, individual flow direction elements are also adjustable by rotating, sliding, bending or other mechanical manipulation, in order to provide additional flow regulation. In these embodiments, some flow direction structures operate as valves or provide analogous variable-area component functions. -
FIGS. 4A and 4B are perspective views ofairfoil insert 10 with indirect-flow convection apertures 41. In these embodiments, insert 10 comprisescontact element 14 withcollar 31 andinlet 32 for directing cooling flow C to the interior ofinsert wall 11, andindirect convection apertures 41 for converting the interior flow to convective flow c along the exterior ofinsert wall 11. - Indirect
convective flow apertures 41 are formed intoinsert wall 11 downstream ofinlet 32, using one or more of the mechanical techniques described above. In contrast to direct-flow apertures, however, which direct convective flow aroundinsert wall 11, indirect-flow apertures 41 generate flow throughinsert wall 11, converting the internal (non-convective) flow insideinsert 10 to an external (convective) flow on the outside ofinsert 10. - The number, sizes, shapes and locations of indirect-
flow apertures 41 vary, depending upon the desired convective flow rate alonginsert wall 11. In the embodiment ofFIG. 4A , for example, a number of substantiallyrectangular apertures 41 are formed in an upstream region ofinsert wall 11, proximatefirst end 12. InFIG. 4B , supplementalconvective flow apertures 41 are also formed between first (upstream)end 12 and second (downstream)end 13. In further embodiments,apertures 41 are formed with circular, oval, triangular, slotted or other geometries, in order to provide desired rates of convective flow for a range of different airfoil and cooling passage geometries. -
Convective flow apertures 41 are distinguished from impingement holes and related structures, which direct relatively high-pressure flow away frominsert wall 11 in order to impinge on interior airfoil surfaces. In contrast, insert 10 maintains a relatively low overpressure, so that the flow throughapertures 41 is generated with a generally parallel sense along the exterior ofinsert wall 11. This produces a substantially convective flow, rather than an impingement flow. Similarly, direct flow apertures 37 (above) generate convective flow that is directed alonginsert wall 11, rather than impingement jets that are directed away frominsert wall 11 and toward interior surfaces of the airfoil. - In the embodiment of
FIG. 4A ,outlet 42 is formed indownstream end 13 ofinsert wall 11 via techniques similar to those described above forinlet 32.Outlet 42 converts the internal flow to downstream flow D, which supplies a downstream cooling load such as a serpentine cooling passage, a platform or shroud cooling system, or another airfoil. In contrast to designs that commingle the convective and downstream flows, insertwall 11 also provides a shielded cooling flow conduit that isolates the interior (non-convective) flow from the exterior (convective) flow. This allowsinsert 10 to generate downstream flow D at lower temperatures than non-shielded designs, further improving cooling efficiency. - Alternatively, insert 10 is provided with
downstream flow stop 36, as shown inFIG. 4B . In this embodiment, flow stop 36 stops flow through the interior ofinsert 10, and directs additional convective flow along the exterior ofinsert wall 11. - The cross-sectional profile of
insert 10 is configurable to control heat pick up and absorption, to augment heat transfer, and to limit pressure losses along the internal cooling passage, while maintaining a positive overpressure withininsert wall 11. Thus insert 10 and insertwall 11 take on a variety of shapes and forms. - In
FIG. 2A , for example, insert 10 exhibits a relatively regular oval or oblate geometry, which does not necessarily conform to the surface of the cooling passage. InFIGS. 4A and 4B , insertwall 11 exhibits a taper, such that the cross section decreases betweenupstream end 12 anddownstream end 13. Alternatively, insertwall 11 conforms to the interior of the cooling passage, as shown inFIGS. 3A and 3B . In these embodiments, insert 10 sometimes accommodates bends or angles along the cooling passage, as shown inFIG. 1 , so that the spacing betweeninsert wall 11 and the internal airfoil surfaces is closely controlled. This allowsinsert 10 to perform the functions of a secondary or cast-in wall, but with significantly less manufacturing complexity and cost than other designs.Insert 10 is also configurable to be removable for maintenance and repair, while cast-in walls are typically permanent structures. - In each of the above embodiments, insert 10 exhibits a generally closed geometry in which insert
wall 11 has a generally tubular or annular cross section, which forms a substantially complete perimeter boundary between the interior (non-convective) and exterior (convective) regions. In other embodiments, insertwall 11 exhibits an open configuration, in which the boundary extends to at least one interior surface of the airfoil.FIGS. 5A and 5B are a top schematic view and a perspective view, respectively, of U-shaped (open-geometry) insert 10 forairfoil section 21. In this embodiment, insertwall 11 comprises a unitary structure with a substantially open U-shaped or C-shaped cross section. As shown inFIG. 5A , insert 10 is spaced frominternal surfaces 27 viaribs 38. In this embodiment, contact elements are formed along the extent ofinsert wall 11, where itcontacts ribs 38, and insert 10contacts airfoil section 21 at seals 51. - The overpressure within
insert wall 11 is maintained via seals 5l alonginternal surface 27 of coolingpassage 26A, which complete the boundary between the interior (non-convective) and exterior (convective) flow regions ofinsert 10. The seals typically extend fromfirst end 12 tosecond end 13 of insert wall 11 (seeFIG. 5B ). -
Flow stop 36 works in cooperation withseals 51 to direct flow fromfeed 52 throughapertures 37, but restricts convective flow tointernal surfaces 27 of coolingpassage 26A opposite leadingedge 24,pressure side 33 andsuction side 34. This increases cooling efficiency by reducing flow along the interior wall betweencooling passages -
FIGS. 6A and 6B are a top schematic view and a perspective view, respectively, of two-panel (open-geometry) insert 10 forairfoil section 21. In this embodiment, insertwall 11 comprises a two-panel structure with a substantially open cross section. - As shown in
FIG. 6A , insert 10contacts airfoil section 21 along fourseals 51, which extend alonginsert wall 11 fromfirst end 12 to second end 13 (seeFIG. 6B ). Convective flow fromfeed 52 is directed alongmidbody cooling channel 26B throughapertures 37, and restricted to internal airfoil surfaces 27opposite pressure side 33 andsuction side 34. This reduces flow along the interior walls betweenchannel 26B andcooling passages - The present invention has been described with reference to preferred embodiments. The terminology used is for the purposes of description, not limitation, and workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention.
Claims (35)
1. An airfoil insert comprising:
an insert wall defining an interior extending inside the insert wall from a first end to a second end, and an exterior extending outside the insert wall from the first end to the second end;
a contact element formed on the exterior of the insert wall; and
a flow director formed on the insert wall at a boundary between the interior and the exterior, wherein the flow director increases a heat transfer coefficient of convective flow along the insert wall by directing the convective flow to the exterior of the insert wall.
2. The insert of claim 1 , wherein the contact element comprises a collar for spacing the insert wall from an internal cooling passage of an airfoil.
3. The insert of claim 1 , wherein the flow director comprises convection flow apertures for directing the convective flow to the exterior of the insert wall.
4. The insert of claim 3 , wherein the contact element comprises tabs for spacing the insert wall from an internal cooling passage of an airfoil.
5. The insert of claim 4 , wherein the tabs define the convection flow apertures therebetween.
6. The insert of claim 3 , wherein the flow director comprises an inlet for conducting flow to the interior of the insert wall.
7. The insert of claim 6 , wherein the convection flow apertures are formed in the insert wall.
8. The insert of claim 6 , further comprising an outlet formed in the second end of the insert wall, for conducting flow from the interior of the insert wall to a downstream cooling load.
9. The insert of claim 1 , wherein the flow director comprise a stop for stopping flow through the interior of the insert wall.
10. The insert of claim 1 , further comprising a flame spray coating on the insert wall for attaching the insert along an internal cooling passage of an airfoil.
11. The insert of claim 1 , wherein the insert wall has a closed cross-sectional geometry.
12. The insert of claim 1 , wherein the insert wall has an open cross-sectional geometry formed by a unitary U-shaped or C-shaped structure.
13. The insert of claim 1 , wherein the insert wall has an open cross-sectional geometry formed by two panels.
14. An airfoil comprising:
an airfoil section comprising a leading edge, a trailing edge, pressure and suction surfaces defined between the leading edge and the trailing edge, and an inner surface defining an internal cooling passage; and
an insert comprising an insert wall and a flow director for restricting convective flow to a region between the insert wall and the inner surface of the airfoil section.
15. The airfoil of claim 14 , wherein the flow director increases a Reynolds number of the convective flow.
16. The airfoil of claim 14 , wherein the flow director increases a Mach number of the convective flow.
17. The airfoil of claim 14 , further comprising augmentors formed along the internal cooling passage to augment convective heat transfer along the inner surface of the airfoil section.
18. The airfoil of claim 17 , wherein the augmentors comprise at least one of trip strips, turbulators, pins, dimples, warts and pedestals.
19. The airfoil of claim 14 , further comprising a plurality of ribs, pin-fins or other stand-off features of various cross section, formed along the internal cooling passage for spacing the insert wall from the inner surface of the airfoil section.
20. The airfoil of claim 14 , further comprising a contact element formed on an exterior of the insert wall for spacing the insert wall from the inner surface of the airfoil section.
21. The airfoil of claim 14 , wherein the flow director comprises a convection flow aperture for directing convective flow to the region between the insert wall and the inner surface of the airfoil.
22. The airfoil of claim 21 , wherein the flow director further comprises an inlet for conducting flow into an interior of the insert wall.
23. The airfoil of claim 22 , wherein the convection flow aperture is formed in the insert wall.
24. The airfoil of claim 22 , further comprising an outlet for conducting flow from the interior of the insert wall to a downstream cooling load.
25. The airfoil of claim 14 , wherein the flow director further comprises a flow stop for stopping flow through an interior of the insert wall.
26. The airfoil of claim 14 , wherein the insert wall has a substantially closed cross-sectional geometry.
27. The airfoil of claim 14 , wherein the insert wall has a substantially open cross-sectional geometry and forms a seal against the internal cooling passage.
28. The airfoil of claim 14 , further comprising a platform for attaching the airfoil to a stationary component of a turbine.
29. The airfoil of claim 14 , further comprising a root for attaching the airfoil to a rotating component of a turbine.
30. A method for cooling an airfoil, the method comprising:
positioning an insert along an internal surface of the airfoil;
spacing the insert from the internal surface; and
restricting convective flow along the insert to a region between the insert and the internal surface, such that a Reynolds number of the convective flow is increased.
31. The method of claim 30 , further comprising directing non-convective flow into an interior of the insert.
32. The method of claim 31 , further comprising converting the non-convective flow to the convective flow.
33. The method of claim 31 , further comprising conducting the non-convective flow to a downstream cooling load.
34. The method of claim 30 , further comprising forming augmentors on the internal surface of the airfoil to augment the convective cooling.
35. The method of claim 30 , further comprising attaching the insert to the airfoil such that the insert functions as a cast-in wall.
Priority Applications (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/200,160 US20100054915A1 (en) | 2008-08-28 | 2008-08-28 | Airfoil insert |
EP09252079A EP2159376A3 (en) | 2008-08-28 | 2009-08-27 | Airfoil insert and method for cooling an airfoil |
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US12/200,160 US20100054915A1 (en) | 2008-08-28 | 2008-08-28 | Airfoil insert |
Publications (1)
Publication Number | Publication Date |
---|---|
US20100054915A1 true US20100054915A1 (en) | 2010-03-04 |
Family
ID=41203644
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US12/200,160 Abandoned US20100054915A1 (en) | 2008-08-28 | 2008-08-28 | Airfoil insert |
Country Status (2)
Country | Link |
---|---|
US (1) | US20100054915A1 (en) |
EP (1) | EP2159376A3 (en) |
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US10774657B2 (en) | 2018-11-23 | 2020-09-15 | Raytheon Technologies Corporation | Baffle assembly for gas turbine engine components |
US11346248B2 (en) * | 2020-02-10 | 2022-05-31 | General Electric Company Polska Sp. Z O.O. | Turbine nozzle segment and a turbine nozzle comprising such a turbine nozzle segment |
US11480060B2 (en) * | 2020-03-06 | 2022-10-25 | Doosan Heavy Industries & Construction Co., Ltd. | Turbomachine component for a gas turbine, turbomachine assembly and gas turbine having the same |
Also Published As
Publication number | Publication date |
---|---|
EP2159376A3 (en) | 2012-03-21 |
EP2159376A2 (en) | 2010-03-03 |
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