US20240011400A1 - Airfoil with baffle having flange ring affixed to platform - Google Patents
Airfoil with baffle having flange ring affixed to platform Download PDFInfo
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- US20240011400A1 US20240011400A1 US18/191,016 US202318191016A US2024011400A1 US 20240011400 A1 US20240011400 A1 US 20240011400A1 US 202318191016 A US202318191016 A US 202318191016A US 2024011400 A1 US2024011400 A1 US 2024011400A1
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- airfoil
- tube
- weld joint
- platform
- attachment portion
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Images
Classifications
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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
-
- 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
- F05D2230/00—Manufacture
- F05D2230/20—Manufacture essentially without removing material
- F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
- F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
- F05D2230/234—Laser welding
-
- 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
- F05D2230/00—Manufacture
- F05D2230/50—Building or constructing in particular ways
- F05D2230/51—Building or constructing in particular ways in a modular way, e.g. using several identical or complementary parts or features
-
- 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
- F05D2240/20—Rotors
- F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
- F05D2240/301—Cross-sectional characteristics
-
- 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
-
- 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
- a gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section.
- the compressor section typically includes low and high pressure compressors, and the turbine section includes low and high pressure turbines.
- the high pressure turbine drives the high pressure compressor through an outer shaft to form a high spool
- the low pressure turbine drives the low pressure compressor through an inner shaft to form a low spool.
- the fan section may also be driven by the low inner shaft.
- a direct drive gas turbine engine includes a fan section driven by the low spool such that the low pressure compressor, low pressure turbine and fan section rotate at a common speed in a common direction.
- An airfoil includes an airfoil section that has an airfoil wall that defines leading and trailing ends and first and second sides that joins the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends.
- the airfoil wall circumscribes an internal core cavity.
- a platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region circumscribing the opening.
- a baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring affixed to the platform at the land region.
- the tube and the attachment portion are connected to each other at a weld joint.
- the tube and the attachment portion overlap at the weld joint.
- the weld joint is continuous around the tube.
- the tube and the tapered neck portion overlap at the weld joint.
- the tube defines a first tube end and a second tube end.
- the first tube end is connected in the weld joint, and further includes a cover connected to the second tube end.
- the flange ring has four perimeter apexes.
- the attachment portion includes a tapered neck portion, and the tapered neck portion and the tube are connected to each other at a weld joint.
- a gas turbine engine includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor.
- the turbine section has a turbine airfoil according to any of the foregoing embodiments.
- FIG. 1 illustrates an example gas turbine engine.
- FIG. 2 illustrates an airfoil of the engine of FIG. 1 .
- FIG. 3 illustrated a sectioned view of the airfoil of FIG. 2 .
- FIG. 4 A illustrates an isolated view of a baffle of the airfoil from FIG. 2 .
- FIG. 4 B illustrates an expanded view of the baffle of FIG. 4 A .
- FIG. 5 illustrates a sectioned view through a weld joint of the baffle of FIG. 4 A .
- FIG. 6 illustrates a sectioned view of a portion of the platform, airfoil section, and baffle of the airfoil of FIG. 2 .
- FIG. 7 A illustrates an isolated view of another example baffle.
- FIG. 7 B illustrates an expanded view of the baffle of FIG. 7 A .
- FIG. 1 schematically illustrates a gas turbine engine 20 .
- the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22 , a compressor section 24 , a combustor section 26 and a turbine section 28 .
- the fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15 , and also drives air along a core flow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28 .
- the exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38 . It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
- the low speed spool 30 generally includes an inner shaft 40 that interconnects, a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46 .
- the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive a fan 42 at a lower speed than the low speed spool 30 .
- the high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54 .
- a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54 .
- a mid-turbine frame 57 of the engine static structure 36 may be arranged generally between the high pressure turbine 54 and the low pressure turbine 46 .
- the mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28 .
- the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
- the core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52 , mixed and burned with fuel in the combustor 56 , then expanded over the high pressure turbine 54 and low pressure turbine 46 .
- the mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C.
- the turbines 46 , 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion. It will be appreciated that each of the positions of the fan section 22 , compressor section 24 , combustor section 26 , turbine section 28 , and fan drive gear system 48 may be varied.
- gear system 48 may be located aft of the low pressure compressor, or aft of the combustor section 26 or even aft of turbine section 28 , and fan 42 may be positioned forward or aft of the location of gear system 48 .
- the engine 20 in one example is a high-bypass geared aircraft engine.
- the engine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10)
- the geared architecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3
- the low pressure turbine 46 has a pressure ratio that is greater than about five.
- the engine 20 bypass ratio is greater than about ten (10:1)
- the fan diameter is significantly larger than that of the low pressure compressor 44
- the low pressure turbine 46 has a pressure ratio that is greater than about five 5:1.
- Low pressure turbine 46 pressure ratio is pressure measured prior to inlet of low pressure turbine 46 as related to the pressure at the outlet of the low pressure turbine 46 prior to an exhaust nozzle.
- the geared architecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1 and less than about 5:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans.
- the fan section 22 of the engine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,668 meters).
- TSFC Thrust Specific Fuel Consumption
- Low fan pressure ratio is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system.
- the low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45.
- Low corrected fan tip speed is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)] ⁇ circumflex over ( ) ⁇ 5.
- the “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 meters/second).
- FIG. 2 illustrates a representative example of a turbine airfoil 60 used in the turbine engine 20 (see also FIG. 1 ), and FIG. 3 illustrates a sectioned view of the airfoil 60 .
- the turbine airfoil 60 is a turbine vane; however, it is to be understood that, although the examples herein may be described with reference to the turbine vane, this disclosure is also applicable to turbine blades.
- the turbine airfoil 60 includes an outer or first platform 62 , an inner or second platform 64 , and an airfoil section 66 that spans in a longitudinal direction A1 (which is also a radial direction relative to the engine central axis A) between the first and second platforms 62 / 64 .
- Terms such as “radially,” “axially,” or variations thereof are used herein to designate directionality with respect to the engine central axis A.
- the airfoil section 66 includes an airfoil outer wall 68 that delimits the profile of the airfoil section 66 .
- the outer wall 68 defines a leading end 68 a , a trailing end 68 b , and first and second sides 68 c / 68 d that join the leading and trailing ends 68 a / 68 b .
- the first and second sides 68 c / 68 d span in the longitudinal direction between first and second ends 68 e / 68 f .
- the first and second ends 68 e / 68 f are attached, respectively, to the first and second platforms 62 / 64 .
- the first side 68 c is a pressure side and the second side 68 d is a suction side.
- the outer wall 68 circumscribes an internal core cavity 70 .
- the airfoil section 66 includes a rib 72 that extends from the first side 68 c to the second side 68 d and partitions the cavity 70 into a forward core cavity 70 a and an aft core cavity 70 b.
- a baffle 74 is disposed in the internal core cavity 70 .
- the baffle 74 is in the forward core cavity 70 a .
- cooling air such as bleed air from the compressor section 24
- the baffle 74 facilitates distribution of the cooling air in the forward core cavity 70 a to cool the outer wall 68 at and near the leading end 68 a .
- the baffle 74 may include impingement orifices through which the cooling air flows to impinge on the inside surface of the outer wall 68 for cooling.
- FIG. 4 A shows an isolated view of the baffle 74
- FIG. 4 B shows an expanded view of the various sections of the baffle 74
- the baffle 74 is formed at least of a tube 76 and an attachment portion 78 .
- the tube 76 , attachment portion 78 , and cover 80 may be made of a metallic alloy, such as a nickel- or cobalt-based alloy.
- the tube 76 has a shape that is generally congruent with the shape of the forward core cavity 70 a .
- the tube 76 includes a first tube end 76 a and a second tube end 76 b .
- the attachment portion 78 includes a flange ring 82 that circumscribes an open central region 84 .
- the flange ring 82 is a continuous or endless band that circumscribes the open central region 84 .
- the attachment portion 78 also includes a tapered neck portion 86 .
- the tapered neck portion 86 is a funnel or funnel-shaped.
- the tube 76 and the attachment portion 78 are connected to each other at a weld joint 88 .
- the tapered neck portion 86 is connected to the first tube end 76 a of the tube 76 at the weld joint 88
- the weld joint 88 is continuous around the tube 76 .
- FIG. 5 illustrates a sectioned view through a representative portion of the weld joint 88 .
- the weld joint 88 may include a weld bead 88 a that bonds the tapered neck portion 86 and the tube 76 together.
- the weld bead 88 a may be a weld material that is provided separately from the attachment portion 78 and the tube 76 during a welding process, or an amalgamation of the material of the attachment portion 78 and the tube 76 from melting during a welding process.
- the weld joint 88 provides a continuous, airtight bond and seal between the tube 76 and the attachment portion 78 .
- the tube 76 and the tapered neck portion 86 of the attachment portion 78 overlap at the weld joint 88 . Such an overlap may facilitate strengthening of the region of the weld joint 88 .
- the tapered neck portion 86 is outside of the tube 76 .
- the tube 76 may be outside of the tapered neck portion 86 .
- the cover 80 is connected to the second tube end 76 b .
- the cover 80 is welded to the tube 76 at another weld joint 89 ( FIG. 4 A ).
- FIG. 6 illustrates a sectioned view through a representative portion of the airfoil section 66 , first platform 62 , and baffle 74 to demonstrate how the baffle 74 is affixed in the airfoil 60 .
- the first platform 62 includes an opening 90 that opens into the internal core cavity 70 (the forward core cavity 70 a in this example).
- the land region 62 a is a relatively smooth band around the opening 90 .
- the tube 76 of the baffle 74 extends in the forward core cavity 70 a.
- the flange ring 82 of the attachment portion 78 is congruent or substantially congruent with the land region 62 a .
- the land region 62 a may be contoured and thus the flange ring 82 may be identically contoured.
- the flange ring 82 is affixed to the first platform 62 at the land region 62 a .
- the flange ring 82 is welded at a weld joint 82 a to the land region 62 a .
- the weld joint 82 a is endless around the flange ring 82 and land region 62 a to provide a continuous, airtight bond there between.
- the weld joint 82 a may be formed by laser welding.
- the continuous, relatively smooth shape of the flange ring 82 facilitates laser welding in comparison to complex geometries that include many low angle corners.
- the flange ring 82 has only rounded perimeter apexes, designated at 82 b .
- the flange ring 82 has four edge perimeter apexes 82 b , which facilitates laser welding in comparison to baffles that have tabs around the perimeter and thus many corners.
- the weld joint 82 a may include a weld bead that bonds the flange ring 82 and the land region 62 a together.
- the baffle 74 is positioned with a gap between the baffle 74 and the outer wall 68 . Most typically, this gap will be uniform or substantially uniform throughout the forward core cavity 70 a . The gap provides an impingement stand-off distance to facilitate impingement cooling.
- the components of the baffle 74 may be formed using several manufacturing techniques. For example, pressure-forming involves using a fluid pressure to force a sheet of material into the shape of an adjacent mold. Pressure-forming is not conducive to forming highly contoured sections like the flange ring 82 . Pressure-forming, which is conducive to forming relatively simple shapes, can be used to form the tube 76 . Deep drawing involves using tensile stress to stretch and plastically deform a metal stock workpiece. Deep drawing, which is conducive to forming highly contoured shapes, can be used to form the contoured shape of the attachment portion 78 .
- the tube 76 and the attachment portion 78 may be formed using different metalworking processes but can then be welded together at the weld joint 88 , such as by laser welding.
- the cover 80 may also be welded to the tube 76 .
- the baffle 74 can then be installed into the airfoil 60 and laser welded to the land region 62 a of the first platform 62 .
- the baffle 74 has only the single weld joint 88 and no other weld seams. Additionally, the congruent shape of the flange ring 82 and the land region 62 a permits laser welding, thereby providing complete sealing between the baffle 74 and the platform 62 .
- FIG. 7 A shows an isolated view of another example baffle 174
- FIG. 7 B shows an expanded view of the various sections of the baffle 174
- like reference numerals designate like elements where appropriate and reference numerals with the addition of one-hundred or multiples thereof designate modified elements that are understood to incorporate the same features and benefits of the corresponding elements.
- the baffle 174 is formed at least of a tube 176 and an attachment portion 178 .
- the tube 176 includes a first tube end 176 a and a second tube end 176 b .
- the first tube end 176 a is a flared end.
- the attachment portion 178 also does not have the tapered neck portion 86 of the attachment portion 78 . Rather, the funnel or funnel-like shape is provided by the flared first end 176 a of the tube 176 .
- the flared first end 176 a is connected directly to the flange ring 82 of the attachment portion 178 at the weld joint 88 .
- the tube 176 and the attachment portion 178 may overlap, similar to as shown in FIG. 5 .
Abstract
An airfoil includes an airfoil section that has an airfoil wall that defines leading and trailing ends and first and second sides that join the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region that circumscribes the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring that is affixed to the platform at the land region.
Description
- A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. Air entering the compressor section is compressed and delivered into the combustion section where it is mixed with fuel and ignited to generate a high-speed exhaust gas flow. The high-speed exhaust gas flow expands through the turbine section to drive the compressor and the fan section. The compressor section typically includes low and high pressure compressors, and the turbine section includes low and high pressure turbines.
- The high pressure turbine drives the high pressure compressor through an outer shaft to form a high spool, and the low pressure turbine drives the low pressure compressor through an inner shaft to form a low spool. The fan section may also be driven by the low inner shaft. A direct drive gas turbine engine includes a fan section driven by the low spool such that the low pressure compressor, low pressure turbine and fan section rotate at a common speed in a common direction.
- An airfoil according to an example of the present disclosure includes an airfoil section that has an airfoil wall that defines leading and trailing ends and first and second sides that joins the leading and trailing ends. The first and second sides span in a longitudinal direction between first and second ends. The airfoil wall circumscribes an internal core cavity. A platform is attached with the first end of the airfoil wall. The platform includes an opening that opens into the internal core cavity and a land region circumscribing the opening. A baffle is formed of a tube and an attachment portion. The tube extends in the internal core cavity and the attachment portion has a flange ring affixed to the platform at the land region.
- In a further embodiment of any of the foregoing embodiments, the tube and the attachment portion are connected to each other at a weld joint.
- In a further embodiment of any of the foregoing embodiments, the tube and the attachment portion overlap at the weld joint.
- In a further embodiment of any of the foregoing embodiments, the weld joint is continuous around the tube.
- In a further embodiment of any of the foregoing embodiments, the attachment portion includes a tapered neck portion, and the tapered neck portion is connected to the tube at the weld joint.
- In a further embodiment of any of the foregoing embodiments, the tube and the tapered neck portion overlap at the weld joint.
- In a further embodiment of any of the foregoing embodiments, the tube defines a first tube end and a second tube end. The first tube end is connected in the weld joint, and further includes a cover connected to the second tube end.
- In a further embodiment of any of the foregoing embodiments, the flange ring has four perimeter apexes.
- In a further embodiment of any of the foregoing embodiments, the attachment portion includes a tapered neck portion, and the tapered neck portion and the tube are connected to each other at a weld joint.
- A gas turbine engine according to an example of the present disclosure includes a compressor section, a combustor in fluid communication with the compressor section, and a turbine section in fluid communication with the combustor. The turbine section has a turbine airfoil according to any of the foregoing embodiments.
- The various features and advantages of the present disclosure will become apparent to those skilled in the art from the following detailed description. The drawings that accompany the detailed description can be briefly described as follows.
-
FIG. 1 illustrates an example gas turbine engine. -
FIG. 2 illustrates an airfoil of the engine ofFIG. 1 . -
FIG. 3 illustrated a sectioned view of the airfoil ofFIG. 2 . -
FIG. 4A illustrates an isolated view of a baffle of the airfoil fromFIG. 2 . -
FIG. 4B illustrates an expanded view of the baffle ofFIG. 4A . -
FIG. 5 illustrates a sectioned view through a weld joint of the baffle ofFIG. 4A . -
FIG. 6 illustrates a sectioned view of a portion of the platform, airfoil section, and baffle of the airfoil ofFIG. 2 . -
FIG. 7A illustrates an isolated view of another example baffle. -
FIG. 7B illustrates an expanded view of the baffle ofFIG. 7A . -
FIG. 1 schematically illustrates agas turbine engine 20. Thegas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates afan section 22, acompressor section 24, acombustor section 26 and aturbine section 28. Thefan section 22 drives air along a bypass flow path B in a bypass duct defined within anacelle 15, and also drives air along a core flow path C for compression and communication into thecombustor section 26 then expansion through theturbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. - The
exemplary engine 20 generally includes alow speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing systems 38. It should be understood thatvarious bearing systems 38 at various locations may alternatively or additionally be provided, and the location ofbearing systems 38 may be varied as appropriate to the application. - The
low speed spool 30 generally includes aninner shaft 40 that interconnects, a first (or low)pressure compressor 44 and a first (or low)pressure turbine 46. Theinner shaft 40 is connected to thefan 42 through a speed change mechanism, which in exemplarygas turbine engine 20 is illustrated as a gearedarchitecture 48 to drive afan 42 at a lower speed than thelow speed spool 30. The high speed spool 32 includes anouter shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high)pressure turbine 54. Acombustor 56 is arranged inexemplary gas turbine 20 between the high pressure compressor 52 and thehigh pressure turbine 54. Amid-turbine frame 57 of the enginestatic structure 36 may be arranged generally between thehigh pressure turbine 54 and thelow pressure turbine 46. Themid-turbine frame 57 further supports bearingsystems 38 in theturbine section 28. Theinner shaft 40 and theouter shaft 50 are concentric and rotate viabearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes. - The core airflow is compressed by the
low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in thecombustor 56, then expanded over thehigh pressure turbine 54 andlow pressure turbine 46. Themid-turbine frame 57 includesairfoils 59 which are in the core airflow path C. Theturbines low speed spool 30 and high speed spool 32 in response to the expansion. It will be appreciated that each of the positions of thefan section 22,compressor section 24,combustor section 26,turbine section 28, and fandrive gear system 48 may be varied. For example,gear system 48 may be located aft of the low pressure compressor, or aft of thecombustor section 26 or even aft ofturbine section 28, andfan 42 may be positioned forward or aft of the location ofgear system 48. - The
engine 20 in one example is a high-bypass geared aircraft engine. In a further example, theengine 20 bypass ratio is greater than about six (6), with an example embodiment being greater than about ten (10), the gearedarchitecture 48 is an epicyclic gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3 and thelow pressure turbine 46 has a pressure ratio that is greater than about five. In one disclosed embodiment, theengine 20 bypass ratio is greater than about ten (10:1), the fan diameter is significantly larger than that of thelow pressure compressor 44, and thelow pressure turbine 46 has a pressure ratio that is greater than about five 5:1.Low pressure turbine 46 pressure ratio is pressure measured prior to inlet oflow pressure turbine 46 as related to the pressure at the outlet of thelow pressure turbine 46 prior to an exhaust nozzle. The gearedarchitecture 48 may be an epicycle gear train, such as a planetary gear system or other gear system, with a gear reduction ratio of greater than about 2.3:1 and less than about 5:1. It should be understood, however, that the above parameters are only exemplary of one embodiment of a geared architecture engine and that the present invention is applicable to other gas turbine engines including direct drive turbofans. - A significant amount of thrust is provided by the bypass flow B due to the high bypass ratio. The
fan section 22 of theengine 20 is designed for a particular flight condition—typically cruise at about 0.8 Mach and about 35,000 feet (10,668 meters). The flight condition of 0.8 Mach and 35,000 ft (10,668 meters), with the engine at its best fuel consumption—also known as “bucket cruise Thrust Specific Fuel Consumption (‘TSFC’)”—is the industry standard parameter of lbm of fuel being burned divided by lbf of thrust the engine produces at that minimum point. “Low fan pressure ratio” is the pressure ratio across the fan blade alone, without a Fan Exit Guide Vane (“FEGV”) system. The low fan pressure ratio as disclosed herein according to one non-limiting embodiment is less than about 1.45. “Low corrected fan tip speed” is the actual fan tip speed in ft/sec divided by an industry standard temperature correction of [(Tram ° R)/(518.7° R)]{circumflex over ( )}5. The “Low corrected fan tip speed” as disclosed herein according to one non-limiting embodiment is less than about 1150 ft/second (350.5 meters/second). -
FIG. 2 illustrates a representative example of aturbine airfoil 60 used in the turbine engine 20 (see alsoFIG. 1 ), andFIG. 3 illustrates a sectioned view of theairfoil 60. As shown, theturbine airfoil 60 is a turbine vane; however, it is to be understood that, although the examples herein may be described with reference to the turbine vane, this disclosure is also applicable to turbine blades. - The
turbine airfoil 60 includes an outer orfirst platform 62, an inner orsecond platform 64, and anairfoil section 66 that spans in a longitudinal direction A1 (which is also a radial direction relative to the engine central axis A) between the first andsecond platforms 62/64. Terms such as “radially,” “axially,” or variations thereof are used herein to designate directionality with respect to the engine central axis A. - The
airfoil section 66 includes an airfoilouter wall 68 that delimits the profile of theairfoil section 66. Theouter wall 68 defines aleading end 68 a, a trailingend 68 b, and first andsecond sides 68 c/68 d that join the leading and trailing ends 68 a/68 b. The first andsecond sides 68 c/68 d span in the longitudinal direction between first and second ends 68 e/68 f. The first and second ends 68 e/68 f are attached, respectively, to the first andsecond platforms 62/64. In this example, thefirst side 68 c is a pressure side and thesecond side 68 d is a suction side. As shown inFIG. 3 , theouter wall 68 circumscribes aninternal core cavity 70. In this example, theairfoil section 66 includes arib 72 that extends from thefirst side 68 c to thesecond side 68 d and partitions thecavity 70 into aforward core cavity 70 a and anaft core cavity 70 b. - A
baffle 74 is disposed in theinternal core cavity 70. In this example, thebaffle 74 is in theforward core cavity 70 a. During operation, cooling air, such as bleed air from thecompressor section 24, is provided to thebaffle 74 through thefirst platform 62. Thebaffle 74 facilitates distribution of the cooling air in theforward core cavity 70 a to cool theouter wall 68 at and near the leadingend 68 a. For instance, thebaffle 74 may include impingement orifices through which the cooling air flows to impinge on the inside surface of theouter wall 68 for cooling. -
FIG. 4A shows an isolated view of thebaffle 74, andFIG. 4B shows an expanded view of the various sections of thebaffle 74. Thebaffle 74 is formed at least of atube 76 and anattachment portion 78. In this example, there is also acover 80. Thetube 76,attachment portion 78, and cover 80 may be made of a metallic alloy, such as a nickel- or cobalt-based alloy. - The
tube 76 has a shape that is generally congruent with the shape of theforward core cavity 70 a. Thetube 76 includes a first tube end 76 a and asecond tube end 76 b. Theattachment portion 78 includes aflange ring 82 that circumscribes an opencentral region 84. For instance, theflange ring 82 is a continuous or endless band that circumscribes the opencentral region 84. In this example, theattachment portion 78 also includes a taperedneck portion 86. For instance, the taperedneck portion 86 is a funnel or funnel-shaped. - The
tube 76 and theattachment portion 78 are connected to each other at a weld joint 88. For instance, in this example, the taperedneck portion 86 is connected to the first tube end 76 a of thetube 76 at the weld joint 88, and the weld joint 88 is continuous around thetube 76.FIG. 5 illustrates a sectioned view through a representative portion of the weld joint 88. For example, the weld joint 88 may include aweld bead 88 a that bonds thetapered neck portion 86 and thetube 76 together. Theweld bead 88 a may be a weld material that is provided separately from theattachment portion 78 and thetube 76 during a welding process, or an amalgamation of the material of theattachment portion 78 and thetube 76 from melting during a welding process. The weld joint 88 provides a continuous, airtight bond and seal between thetube 76 and theattachment portion 78. - In this example, the
tube 76 and the taperedneck portion 86 of theattachment portion 78 overlap at the weld joint 88. Such an overlap may facilitate strengthening of the region of the weld joint 88. In this example, the taperedneck portion 86 is outside of thetube 76. However, it is to be understood that alternatively thetube 76 may be outside of the taperedneck portion 86. Thecover 80 is connected to thesecond tube end 76 b. For example, thecover 80 is welded to thetube 76 at another weld joint 89 (FIG. 4A ). -
FIG. 6 illustrates a sectioned view through a representative portion of theairfoil section 66,first platform 62, and baffle 74 to demonstrate how thebaffle 74 is affixed in theairfoil 60. Thefirst platform 62 includes anopening 90 that opens into the internal core cavity 70 (theforward core cavity 70 a in this example). There is aland region 62 a that circumscribes theopening 90. For instance, theland region 62 a is a relatively smooth band around theopening 90. Thetube 76 of thebaffle 74 extends in theforward core cavity 70 a. - The
flange ring 82 of theattachment portion 78 is congruent or substantially congruent with theland region 62 a. For instance, theland region 62 a may be contoured and thus theflange ring 82 may be identically contoured. Theflange ring 82 is affixed to thefirst platform 62 at theland region 62 a. For example, theflange ring 82 is welded at a weld joint 82 a to theland region 62 a. The weld joint 82 a is endless around theflange ring 82 andland region 62 a to provide a continuous, airtight bond there between. The weld joint 82 a may be formed by laser welding. In this regard, the continuous, relatively smooth shape of theflange ring 82 facilitates laser welding in comparison to complex geometries that include many low angle corners. For example, theflange ring 82 has only rounded perimeter apexes, designated at 82 b. In the illustrated example (FIG. 4A ), theflange ring 82 has four edge perimeter apexes 82 b, which facilitates laser welding in comparison to baffles that have tabs around the perimeter and thus many corners. - Similar to the weld joint 88, the weld joint 82 a may include a weld bead that bonds the
flange ring 82 and theland region 62 a together. In the fixed position, thebaffle 74 is positioned with a gap between thebaffle 74 and theouter wall 68. Most typically, this gap will be uniform or substantially uniform throughout theforward core cavity 70 a. The gap provides an impingement stand-off distance to facilitate impingement cooling. - The components of the
baffle 74 may be formed using several manufacturing techniques. For example, pressure-forming involves using a fluid pressure to force a sheet of material into the shape of an adjacent mold. Pressure-forming is not conducive to forming highly contoured sections like theflange ring 82. Pressure-forming, which is conducive to forming relatively simple shapes, can be used to form thetube 76. Deep drawing involves using tensile stress to stretch and plastically deform a metal stock workpiece. Deep drawing, which is conducive to forming highly contoured shapes, can be used to form the contoured shape of theattachment portion 78. Thetube 76 and theattachment portion 78 may be formed using different metalworking processes but can then be welded together at the weld joint 88, such as by laser welding. Thecover 80 may also be welded to thetube 76. Thebaffle 74 can then be installed into theairfoil 60 and laser welded to theland region 62 a of thefirst platform 62. - The
baffle 74 has only the single weld joint 88 and no other weld seams. Additionally, the congruent shape of theflange ring 82 and theland region 62 a permits laser welding, thereby providing complete sealing between thebaffle 74 and theplatform 62. -
FIG. 7A shows an isolated view of anotherexample baffle 174, andFIG. 7B shows an expanded view of the various sections of thebaffle 174. In this disclosure, like reference numerals designate like elements where appropriate and reference numerals with the addition of one-hundred or multiples thereof designate modified elements that are understood to incorporate the same features and benefits of the corresponding elements. Thebaffle 174 is formed at least of atube 176 and anattachment portion 178. - The
tube 176 includes afirst tube end 176 a and asecond tube end 176 b. In this example, thefirst tube end 176 a is a flared end. Theattachment portion 178 also does not have the taperedneck portion 86 of theattachment portion 78. Rather, the funnel or funnel-like shape is provided by the flaredfirst end 176 a of thetube 176. The flaredfirst end 176 a is connected directly to theflange ring 82 of theattachment portion 178 at the weld joint 88. Thetube 176 and theattachment portion 178 may overlap, similar to as shown inFIG. 5 . - Although a combination of features is shown in the illustrated examples, not all of them need to be combined to realize the benefits of various embodiments of this disclosure. In other words, a system designed according to an embodiment of this disclosure will not necessarily include all of the features shown in any one of the Figures or all of the portions schematically shown in the Figures. Moreover, selected features of one example embodiment may be combined with selected features of other example embodiments.
- The preceding description is exemplary rather than limiting in nature. Variations and modifications to the disclosed examples may become apparent to those skilled in the art that do not necessarily depart from this disclosure. The scope of legal protection given to this disclosure can only be determined by studying the following claims.
Claims (10)
1. An airfoil comprising:
an airfoil section having an airfoil wall defining leading and trailing ends and first and second sides joining the leading and trailing ends, the first and second sides spanning in a longitudinal direction between first and second ends, the airfoil wall circumscribing an internal core cavity;
a platform attached with the first end of the airfoil wall, the platform including an opening that opens into the internal core cavity and a land region circumscribing the opening; and
a baffle formed of a tube and an attachment portion, the tube extending in the internal core cavity and the attachment portion having a flange ring affixed to the platform at the land region.
2. The airfoil as recited in claim 1 , wherein the tube and the attachment portion are connected to each other at a weld joint.
3. The airfoil as recited in claim 2 , wherein the tube and the attachment portion overlap at the weld joint.
4. The airfoil as recited in claim 2 , wherein the weld joint is continuous around the tube.
5. The airfoil as recited in claim 2 , wherein the attachment portion includes a tapered neck portion, and the tapered neck portion is connected to the tube at the weld joint.
6. The airfoil as recited in claim 5 , wherein the tube and the tapered neck portion overlap at the weld joint.
7. The airfoil as recited in claim 6 , wherein the tube defines a first tube end and a second tube end, the first tube end is connected in the weld joint, and further comprising a cover connected to the second tube end.
8. The airfoil as recited in claim 1 , wherein the flange ring has four perimeter apexes.
9. The airfoil as recited in claim 8 , wherein the attachment portion includes a tapered neck portion, and the tapered neck portion and the tube are connected to each other at a weld joint.
10. A gas turbine engine comprising:
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor,
the turbine section having a turbine airfoil that includes
an airfoil section having an airfoil wall defining leading and trailing ends and first and second sides joining the leading and trailing ends, the first and second sides spanning in a longitudinal direction between first and second ends, the airfoil wall circumscribing an internal core cavity,
a platform attached with the first end of the airfoil wall, the platform including an opening that opens into the internal core cavity and a land region circumscribing the opening, and
a baffle formed of a tube and a continuous flange, the tube extending in the internal core cavity and the continuous flange being affixed to the platform at the land region.
Priority Applications (1)
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US18/191,016 US20240011400A1 (en) | 2018-11-09 | 2023-03-28 | Airfoil with baffle having flange ring affixed to platform |
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US201862757916P | 2018-11-09 | 2018-11-09 | |
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US18/191,016 US20240011400A1 (en) | 2018-11-09 | 2023-03-28 | Airfoil with baffle having flange ring affixed to platform |
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US18/191,016 Pending US20240011400A1 (en) | 2018-11-09 | 2023-03-28 | Airfoil with baffle having flange ring affixed to platform |
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US11702941B2 (en) | 2023-07-18 |
EP3650640A1 (en) | 2020-05-13 |
EP3650640B1 (en) | 2022-05-11 |
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