US20140241897A1 - Aluminum brazing of hollow titanium fan blades - Google Patents
Aluminum brazing of hollow titanium fan blades Download PDFInfo
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- US20140241897A1 US20140241897A1 US13/625,956 US201213625956A US2014241897A1 US 20140241897 A1 US20140241897 A1 US 20140241897A1 US 201213625956 A US201213625956 A US 201213625956A US 2014241897 A1 US2014241897 A1 US 2014241897A1
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- Prior art keywords
- fan blade
- titanium
- cover
- aluminum alloy
- portions
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/18—Rotors
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
- B23K1/00—Soldering, e.g. brazing, or unsoldering
- B23K1/0008—Soldering, e.g. brazing, or unsoldering specially adapted for particular articles or work
- B23K1/0018—Brazing of turbine parts
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/02—Selection of particular materials
- F04D29/023—Selection of particular materials especially adapted for elastic fluid pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/18—Rotors
- F04D29/20—Mounting rotors on shafts
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
- F04D29/324—Blades
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
- B23P—METAL-WORKING NOT OTHERWISE PROVIDED FOR; COMBINED OPERATIONS; UNIVERSAL MACHINE TOOLS
- B23P15/00—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass
- B23P15/04—Making specific metal objects by operations not covered by a single other subclass or a group in this subclass turbine or like blades from several pieces
-
- 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
- F05D2220/36—Application in turbines specially adapted for the fan of turbofan engines
-
- 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
- F05D2230/237—Brazing
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/13—Refractory metals, i.e. Ti, V, Cr, Zr, Nb, Mo, Hf, Ta, W
- F05D2300/133—Titanium
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/173—Aluminium alloys, e.g. AlCuMgPb
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/10—Metals, alloys or intermetallic compounds
- F05D2300/17—Alloys
- F05D2300/174—Titanium alloys, e.g. TiAl
Definitions
- This disclosure relates to hollow fan blades and a method of brazing the same.
- Titanium-based alloys are widely used for structural applications in the aerospace industry. These alloys provide good fatigue properties, erosion benefits relative to aluminum alloys, and are light weight compared to steel, stainless steels, and nickel alloys. While significant weight savings can be achieved with solid titanium components, even greater weight savings can be achieved using hollow structures.
- Hollow titanium fan blades are typically produced by diffusion bonding two machined cavity-containing plates on the neutral axis, hot forming and inflating the bonded assembly to achieve its final shape within complex dies, and finally post-thermal processing the blade's surface to remove any surface contamination. Much of the part cost is incurred by the complex bonding and forming process.
- brazing titanium with aluminum has been used for decades, but requires a narrow window of time and temperature. This stems from the fact that aluminum and titanium can form brittle intermetallic phases at the joint interface, if line and temperature are not properly controlled.
- a fan blade includes first and second titanium portions that are secured to one another with an aluminum alloy braze.
- the first titanium portion is provided by a forging.
- the first titanium portion includes machined ribs.
- the machined ribs include undercuts that have an arcuate shape.
- the second titanium portion is a hot-formed sheet that provides a cover.
- the fan blade has a blade root defined by the first titanium portion.
- the fan blade has a blade tip defined by the first titanium portion.
- the cover provides one side of the airfoil.
- the first titanium portion includes opposing first and second edges that define the fan blade leading and trailing edges.
- a method of manufacturing a fan blade includes providing first and second titanium portions, applying an aluminum alloy braze to at least one of the first and second titanium portions, and heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour.
- the method includes the step of forging the first titanium portion.
- the method includes the step of machining the first titanium portion.
- the method includes the step of applying the aluminum alloy braze before the machining step.
- the method includes the step of pressing the second titanium portion to produce a cover that provides a side of the airfoil.
- the method includes the step of pickling the cover.
- the method includes the step of applying the aluminum alloy braze after pickling the cover.
- the method includes the step of bagging the first and second titanium portions prior to performing the heating step.
- the method includes the step of purging the bag prior to the heating step.
- the method includes the step of pulling a vacuum on the bag during the heating step.
- the first titanium portion provides a root, a tip and leading and trailing edges of the airfoil exterior contour.
- FIG. 1 is a perspective view of an example brazed titanium fan blade.
- FIG. 2A is a cross-sectional view of the fan blade shown in FIG. 1 taken along line 2 A- 2 A.
- FIG. 2B is an exploded enlarged view of a portion of the fan blade shown in FIG. 2A .
- FIG. 3 is a flow chart depicting an example manufacturing method for the fan blade.
- FIG. 4 schematically depicts the brazing process.
- a fan blade 10 is schematically depicted in FIGS. 1 and 2 .
- the fan blade 10 includes a root 12 supporting an airfoil 14 that extends to a tip 16 .
- First and second titanium portions 18 , 20 are brazed to one another to provide an exterior contour 22 of the fan blade 10 .
- the first titanium portion 18 is provided by a forged blank that is machined to remove material 24 .
- Ribs 26 are provided that have undercuts 28 with an arcuate shape and within the interior of the first titanium portion 18 to reduce weight while providing fan blade structural integrity, ensuring blade fatigue life, and supporting the airfoil cover 20 .
- the first titanium portion 18 provides the root 12 and one side of the airfoil 14 along with the tip 16 .
- the first portion 18 also provides first and second edges that define fan blade leading and trailing edges 17 , 19 .
- the second titanium portion 20 provides a cover that is secured over the interior of the first titanium portion 18 by a braze 34 .
- a titanium cover would be used for its thermal expansion match with the titanium forging, its superior corrosion resistance relative to aluminum, its improved stiffness relative to aluminum, its improved erosion resistance relative to aluminum, and its improved foreign object debris/impact resistance relative to aluminum.
- the braze 34 is provided on one or both of the first and second mating surfaces 30 , 32 , which are respectively provided by the first and second titanium portions 18 , 20 .
- the braze 34 is an aluminum alloy, such as Al—Cu—Mn, having less than 3 wt % copper and less than 5 wt % manganese and having a solidus-liquidus range within 1175° F.-1225° F.
- the aluminum or aluminum alloy chosen for brazing would be pre-placed onto either the titanium cover or the titanium forging as a photo etched pre-form or cathodic arc deposited directly onto the titanium cover or the titanium forging.
- the entire surface of the side of the cover being brazed or the side of the forging being brazed would be cathodic arc deposited prior to machining the forging or prior to selective etching the titanium cover to only provide braze material at areas being joined.
- a method 40 of forming the fan blade 10 is schematically illustrated at 40 .
- a titanium forging (first titanium portion 18 ) is provided, as indicated by block 42 .
- the proposed method of construction uses a near net shape titanium forging with certified mechanical properties.
- the titanium forging is machined, as indicated at block 46 , to provide structure similar to that shown in FIGS. 1 and 2 , for example.
- the fan blade design may be tailored such that no internal foam inserts would be needed, although inserts may be used if desired.
- an aluminum alloy braze may be applied, as indicated at block 48 .
- the braze will be provided only on the raised surfaces, which provides the first mating surface 30 , subsequent to machining.
- a titanium cover (second titanium portion 20 ) may be provided, as indicated at block 44 .
- the titanium cover may be hot formed at processing conditions that ensure maintaining its certified mechanical properties, while achieving the desired shape for bonding.
- an aluminum alloy braze may be applied, as indicated at block 52 , to the titanium cover subsequent to pickling, as indicated at block 50 . Pickling provides a contaminant-free surface on the cover.
- the cover is arranged over the titanium forging such that the first and second mating surfaces 30 , 32 engage one another.
- the assembled fan blade 10 is inserted into a bag 64 ( FIG. 4 ), as indicated at block 54 .
- the bag is a metallic bag, which may be constructed from a stainless steel or a nickel alloy foil, for example, that can be sealed.
- the sealed bagged fan blade is loaded into a vacuum compression brazing furnace 62 having a heating element 66 , which is shown in FIG. 4 .
- Oxygen and nitrogen within the bag are evacuated and the bag is backfilled with argon, as indicated at block 56 .
- Evacuation and backfilling may be repeated multiple times to reduce the oxygen and nitrogen to an acceptable concentration within the bag and within the fan blade's internal cavities.
- a negative atmosphere is maintained within the sealed bag.
- the magnitude of the bag's internal negative pressure is such that any positive pressure or vacuum external to the bag always provides force upon the titanium cover 20 and the machined fan blade 10 within the bag 64 , throughout all subsequent heating, brazing and cooling.
- Brazing could occur within a vacuum furnace capable of applying a positive pressure of argon, within an argon retort, within a furnace capable of maintaining a hard vacuum or within a vacuum furnace capable of maintaining a partial pressure of argon.
- vacuum compression brazing furnace 62 is capable of applying a positive pressure of argon to the bagged fan blade 10 during heating to melt the aluminum alloy braze material and during subsequent cooling. If brazing within an argon retort, such an environment would be free of both oxygen and nitrogen to the extent acceptable for producing a finished product within the design criteria but meeting or bettering specified surface contamination requirements.
- brazing would be accomplished by heating parts in a retort or other line-of-sight shielding at 5 ⁇ 10-4 torr or lower pressure within a temperature range of 1225° F. to 1290° F. Regardless of the furnace choice, time between 1175° F. on heating and 1175° F. on cooling would be controlled to produce a braze microstructure that conforms to metallurgical standards established by material characterization testing and fan blade component testing. Such standards would control amount of particulate, titanium aluminide, and eutectic intermetallic structure within the braze.
- the aluminum brazing temperature is lower than annealing temperatures used for titanium alloys such as Ti-6-4 and Ti-6-2-4-2, certified mechanical properties of the fan blade cover 20 and the fan blade forging 18 previously created during prior plate/sheet rolling, fan blade forging, and associated follow-on heat treatment will be maintained throughout all aluminum brazing thermal processing.
- the fan blade is then finished, if necessary, as indicated at block 60 .
Abstract
A fan blade includes first and second titanium portions that are secured to one another with an aluminum alloy braze. A method of manufacturing a fan blade includes providing first and second titanium portions, applying an aluminum alloy braze to at least one of the first and second titanium portions, and heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour.
Description
- This disclosure relates to hollow fan blades and a method of brazing the same.
- Titanium-based alloys are widely used for structural applications in the aerospace industry. These alloys provide good fatigue properties, erosion benefits relative to aluminum alloys, and are light weight compared to steel, stainless steels, and nickel alloys. While significant weight savings can be achieved with solid titanium components, even greater weight savings can be achieved using hollow structures.
- It is difficult to create a complicated airfoil shape, especially a hollow fan blade (HFB). Hollow titanium fan blades are typically produced by diffusion bonding two machined cavity-containing plates on the neutral axis, hot forming and inflating the bonded assembly to achieve its final shape within complex dies, and finally post-thermal processing the blade's surface to remove any surface contamination. Much of the part cost is incurred by the complex bonding and forming process.
- Common practice for joining hollow titanium structures is by brazing with titanium-nickel-copper alloys or by diffusion bonding. Brazing titanium with aluminum has been used for decades, but requires a narrow window of time and temperature. This stems from the fact that aluminum and titanium can form brittle intermetallic phases at the joint interface, if line and temperature are not properly controlled.
- In one exemplary embodiment, a fan blade includes first and second titanium portions that are secured to one another with an aluminum alloy braze.
- In a further embodiment of any of the above, the first titanium portion is provided by a forging.
- In a further embodiment of any of the above, the first titanium portion includes machined ribs.
- In a further embodiment of any of the above, the machined ribs include undercuts that have an arcuate shape.
- In a further embodiment of any of the above, the second titanium portion is a hot-formed sheet that provides a cover.
- In a further embodiment of any of the above, the fan blade has a blade root defined by the first titanium portion.
- In a further embodiment of any of the above, the fan blade has a blade tip defined by the first titanium portion.
- In a further embodiment of any of the above, the cover provides one side of the airfoil.
- In a further embodiment of any of the above, the first titanium portion includes opposing first and second edges that define the fan blade leading and trailing edges.
- In another exemplary embodiment, a method of manufacturing a fan blade includes providing first and second titanium portions, applying an aluminum alloy braze to at least one of the first and second titanium portions, and heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour.
- In a further embodiment of any of the above, the method includes the step of forging the first titanium portion.
- In a further embodiment of any of the above, the method includes the step of machining the first titanium portion.
- In a further embodiment of any of the above, the method includes the step of applying the aluminum alloy braze before the machining step.
- In a further embodiment of any of the above, the method includes the step of pressing the second titanium portion to produce a cover that provides a side of the airfoil.
- In a further embodiment of any of the above, the method includes the step of pickling the cover.
- In a further embodiment of any of the above, the method includes the step of applying the aluminum alloy braze after pickling the cover.
- In a further embodiment of any of the above, the method includes the step of bagging the first and second titanium portions prior to performing the heating step.
- In a further embodiment of any of the above, the method includes the step of purging the bag prior to the heating step.
- In a further embodiment of any of the above, the method includes the step of pulling a vacuum on the bag during the heating step.
- In a further embodiment of any of the above, the first titanium portion provides a root, a tip and leading and trailing edges of the airfoil exterior contour.
- The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:
-
FIG. 1 is a perspective view of an example brazed titanium fan blade. -
FIG. 2A is a cross-sectional view of the fan blade shown inFIG. 1 taken alongline 2A-2A. -
FIG. 2B is an exploded enlarged view of a portion of the fan blade shown inFIG. 2A . -
FIG. 3 is a flow chart depicting an example manufacturing method for the fan blade. -
FIG. 4 schematically depicts the brazing process. - A
fan blade 10 is schematically depicted inFIGS. 1 and 2 . Thefan blade 10 includes aroot 12 supporting anairfoil 14 that extends to atip 16. First andsecond titanium portions exterior contour 22 of thefan blade 10. - In the example, the
first titanium portion 18 is provided by a forged blank that is machined to removematerial 24.Ribs 26 are provided that have undercuts 28 with an arcuate shape and within the interior of thefirst titanium portion 18 to reduce weight while providing fan blade structural integrity, ensuring blade fatigue life, and supporting theairfoil cover 20. Thefirst titanium portion 18 provides theroot 12 and one side of theairfoil 14 along with thetip 16. Thefirst portion 18 also provides first and second edges that define fan blade leading andtrailing edges - The
second titanium portion 20 provides a cover that is secured over the interior of thefirst titanium portion 18 by abraze 34. A titanium cover would be used for its thermal expansion match with the titanium forging, its superior corrosion resistance relative to aluminum, its improved stiffness relative to aluminum, its improved erosion resistance relative to aluminum, and its improved foreign object debris/impact resistance relative to aluminum. - The
braze 34 is provided on one or both of the first andsecond mating surfaces second titanium portions braze 34 is an aluminum alloy, such as Al—Cu—Mn, having less than 3 wt % copper and less than 5 wt % manganese and having a solidus-liquidus range within 1175° F.-1225° F. The aluminum or aluminum alloy chosen for brazing would be pre-placed onto either the titanium cover or the titanium forging as a photo etched pre-form or cathodic arc deposited directly onto the titanium cover or the titanium forging. In one example, the entire surface of the side of the cover being brazed or the side of the forging being brazed would be cathodic arc deposited prior to machining the forging or prior to selective etching the titanium cover to only provide braze material at areas being joined. - A
method 40 of forming thefan blade 10 is schematically illustrated at 40. A titanium forging (first titanium portion 18) is provided, as indicated byblock 42. The proposed method of construction uses a near net shape titanium forging with certified mechanical properties. - The titanium forging is machined, as indicated at
block 46, to provide structure similar to that shown inFIGS. 1 and 2 , for example. The fan blade design may be tailored such that no internal foam inserts would be needed, although inserts may be used if desired. Prior to machining (in instances where no metallic foam inserts are used), an aluminum alloy braze may be applied, as indicated atblock 48. Thus, the braze will be provided only on the raised surfaces, which provides thefirst mating surface 30, subsequent to machining. - A titanium cover (second titanium portion 20) may be provided, as indicated at
block 44. The titanium cover may be hot formed at processing conditions that ensure maintaining its certified mechanical properties, while achieving the desired shape for bonding. Alternatively, or in addition to, an aluminum alloy braze may be applied, as indicated atblock 52, to the titanium cover subsequent to pickling, as indicated atblock 50. Pickling provides a contaminant-free surface on the cover. - The cover is arranged over the titanium forging such that the first and second mating surfaces 30, 32 engage one another. The assembled
fan blade 10 is inserted into a bag 64 (FIG. 4 ), as indicated atblock 54. The bag is a metallic bag, which may be constructed from a stainless steel or a nickel alloy foil, for example, that can be sealed. - In one example, the sealed bagged fan blade is loaded into a vacuum
compression brazing furnace 62 having aheating element 66, which is shown inFIG. 4 . Oxygen and nitrogen within the bag are evacuated and the bag is backfilled with argon, as indicated atblock 56. Evacuation and backfilling may be repeated multiple times to reduce the oxygen and nitrogen to an acceptable concentration within the bag and within the fan blade's internal cavities. Following the final evacuation, a negative atmosphere is maintained within the sealed bag. The magnitude of the bag's internal negative pressure is such that any positive pressure or vacuum external to the bag always provides force upon thetitanium cover 20 and the machinedfan blade 10 within the bag 64, throughout all subsequent heating, brazing and cooling. - Brazing could occur within a vacuum furnace capable of applying a positive pressure of argon, within an argon retort, within a furnace capable of maintaining a hard vacuum or within a vacuum furnace capable of maintaining a partial pressure of argon. In the first example, vacuum
compression brazing furnace 62 is capable of applying a positive pressure of argon to the baggedfan blade 10 during heating to melt the aluminum alloy braze material and during subsequent cooling. If brazing within an argon retort, such an environment would be free of both oxygen and nitrogen to the extent acceptable for producing a finished product within the design criteria but meeting or bettering specified surface contamination requirements. If in a standard vacuum furnace, brazing would be accomplished by heating parts in a retort or other line-of-sight shielding at 5×10-4 torr or lower pressure within a temperature range of 1225° F. to 1290° F. Regardless of the furnace choice, time between 1175° F. on heating and 1175° F. on cooling would be controlled to produce a braze microstructure that conforms to metallurgical standards established by material characterization testing and fan blade component testing. Such standards would control amount of particulate, titanium aluminide, and eutectic intermetallic structure within the braze. Because the aluminum brazing temperature is lower than annealing temperatures used for titanium alloys such as Ti-6-4 and Ti-6-2-4-2, certified mechanical properties of thefan blade cover 20 and the fan blade forging 18 previously created during prior plate/sheet rolling, fan blade forging, and associated follow-on heat treatment will be maintained throughout all aluminum brazing thermal processing. The fan blade is then finished, if necessary, as indicated atblock 60. - Although an example embodiment has been disclosed, a worker of ordinary skill in this art would recognize that certain modifications would come within the scope of the claims. For that reason, the following claims should be studied to determine their true scope and content.
Claims (20)
1. A fan blade comprising:
first and second titanium portions are secured to one another with an aluminum alloy braze.
2. The fan blade according to claim 1 , wherein the first titanium portion is provided by a forging.
3. The fan blade according to claim 1 , wherein the first titanium portion includes machined ribs.
4. The fan blade according to claim 3 , wherein the machined ribs include undercuts having an arcuate shape.
5. The fan blade according to claim 1 , wherein the second titanium portion is a hot-formed sheet providing a cover.
6. The fan blade according to claim 2 , wherein the fan blade has a blade root defined by the first titanium portion.
7. The fan blade according to claim 6 , wherein the fan blade has a blade tip defined by the first titanium portion.
8. The fan blade according to claim 7 , wherein the cover provides one side of the airfoil.
9. The fan blade according to claim 8 , wherein the first titanium portion includes opposing first and second edges that define the fan blade leading and trailing edges.
10. A method of manufacturing a fan blade comprising:
providing first and second titanium portions;
applying an aluminum alloy braze to at least one of the first and second titanium portions; and
heating the fan blade to melt the aluminum alloy braze and join the first and second portions to one another to provide a fan blade with an airfoil exterior contour.
11. The method according to claim 10 , comprising the step of forging the first titanium portion.
12. The method according to claim 10 , comprising the step of machining the first titanium portion.
13. The method according to claim 10 , comprising the step of applying the aluminum alloy braze before the machining step.
14. The method according to claim 10 , comprising the step of pressing the second titanium portion to produce a cover providing a side of the airfoil.
15. The method according to claim 14 , comprising the step of pickling the cover.
16. The method according to claim 15 , comprising the step of applying the aluminum alloy braze after pickling the cover.
17. The method according to claim 10 , comprising the step of bagging the first and second titanium portions prior to performing the heating step.
18. The method according to claim 17 , comprising the step of purging the bag prior to the heating step.
19. The method according to claim 18 , comprising the step of pulling a vacuum on the bag during the heating step.
20. The method according to claim 10 , wherein the first titanium portion provides a root, a tip and leading and trailing edges of the airfoil exterior contour.
Priority Applications (5)
Application Number | Priority Date | Filing Date | Title |
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US13/625,956 US20140241897A1 (en) | 2012-09-25 | 2012-09-25 | Aluminum brazing of hollow titanium fan blades |
JP2015533291A JP6170159B2 (en) | 2012-09-25 | 2013-09-25 | Aluminum brazing of hollow titanium fan blades |
PCT/US2013/061571 WO2014099067A2 (en) | 2012-09-25 | 2013-09-25 | Aluminum brazing of hollow titanium fan blades |
EP13864424.0A EP2901023B1 (en) | 2012-09-25 | 2013-09-25 | Aluminum brazing of hollow titanium fan blades |
US15/928,246 US20180216626A1 (en) | 2012-09-25 | 2018-03-22 | Aluminum brazing of hollow titanium fan blades |
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US13/625,956 US20140241897A1 (en) | 2012-09-25 | 2012-09-25 | Aluminum brazing of hollow titanium fan blades |
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US15/928,246 Continuation US20180216626A1 (en) | 2012-09-25 | 2018-03-22 | Aluminum brazing of hollow titanium fan blades |
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US20140241897A1 true US20140241897A1 (en) | 2014-08-28 |
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US13/625,956 Abandoned US20140241897A1 (en) | 2012-09-25 | 2012-09-25 | Aluminum brazing of hollow titanium fan blades |
US15/928,246 Abandoned US20180216626A1 (en) | 2012-09-25 | 2018-03-22 | Aluminum brazing of hollow titanium fan blades |
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US15/928,246 Abandoned US20180216626A1 (en) | 2012-09-25 | 2018-03-22 | Aluminum brazing of hollow titanium fan blades |
Country Status (4)
Country | Link |
---|---|
US (2) | US20140241897A1 (en) |
EP (1) | EP2901023B1 (en) |
JP (1) | JP6170159B2 (en) |
WO (1) | WO2014099067A2 (en) |
Cited By (12)
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US20180038386A1 (en) * | 2016-08-08 | 2018-02-08 | United Technologies Corporation | Fan blade with composite cover |
CN108757560A (en) * | 2018-06-01 | 2018-11-06 | 四川振强锻造有限责任公司 | A kind of aluminium alloy fan blade and its manufacturing method |
US20180355733A1 (en) * | 2017-06-12 | 2018-12-13 | United Technologies Corporation | Hollow titanium airfoil with titanium coating |
US10329919B2 (en) | 2017-04-07 | 2019-06-25 | United Technologies Corporation | Airfoil structure and method of manufacture |
US10443613B2 (en) | 2017-05-31 | 2019-10-15 | United Technologies Corporation | Hollow fan blade with structural ribs |
US10502064B2 (en) | 2017-08-07 | 2019-12-10 | United Technologies Corporation | Power beam welded cavity-back titanium hollow fan blade |
US10677068B2 (en) | 2018-01-18 | 2020-06-09 | Raytheon Technologies Corporation | Fan blade with filled pocket |
US11174737B2 (en) | 2019-06-12 | 2021-11-16 | Raytheon Technologies Corporation | Airfoil with cover for gas turbine engine |
US11236619B2 (en) | 2019-05-07 | 2022-02-01 | Raytheon Technologies Corporation | Multi-cover gas turbine engine component |
US11248477B2 (en) | 2019-08-02 | 2022-02-15 | Raytheon Technologies Corporation | Hybridized airfoil for a gas turbine engine |
US20220134493A1 (en) * | 2019-02-27 | 2022-05-05 | Safran Aircraft Engines | Assembly of an outlet guide vane for an aircraft turbomachine using an inflatable bladder |
US11346362B2 (en) | 2017-07-25 | 2022-05-31 | Raytheon Technologies Corporation | Processes and tooling associated with diffusion bonding |
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Cited By (16)
Publication number | Priority date | Publication date | Assignee | Title |
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US20180038386A1 (en) * | 2016-08-08 | 2018-02-08 | United Technologies Corporation | Fan blade with composite cover |
US10329919B2 (en) | 2017-04-07 | 2019-06-25 | United Technologies Corporation | Airfoil structure and method of manufacture |
US10443613B2 (en) | 2017-05-31 | 2019-10-15 | United Technologies Corporation | Hollow fan blade with structural ribs |
US10830064B2 (en) | 2017-06-12 | 2020-11-10 | Raytheon Technologies Corporation | Hollow titanium airfoil with titanium coating |
US20180355733A1 (en) * | 2017-06-12 | 2018-12-13 | United Technologies Corporation | Hollow titanium airfoil with titanium coating |
US11346362B2 (en) | 2017-07-25 | 2022-05-31 | Raytheon Technologies Corporation | Processes and tooling associated with diffusion bonding |
US10502064B2 (en) | 2017-08-07 | 2019-12-10 | United Technologies Corporation | Power beam welded cavity-back titanium hollow fan blade |
US10677068B2 (en) | 2018-01-18 | 2020-06-09 | Raytheon Technologies Corporation | Fan blade with filled pocket |
CN108757560A (en) * | 2018-06-01 | 2018-11-06 | 四川振强锻造有限责任公司 | A kind of aluminium alloy fan blade and its manufacturing method |
US20220134493A1 (en) * | 2019-02-27 | 2022-05-05 | Safran Aircraft Engines | Assembly of an outlet guide vane for an aircraft turbomachine using an inflatable bladder |
US11833628B2 (en) * | 2019-02-27 | 2023-12-05 | Safran Aircraft Engines | Assembly of an outlet guide vane for an aircraft turbomachine using an inflatable bladder |
US11236619B2 (en) | 2019-05-07 | 2022-02-01 | Raytheon Technologies Corporation | Multi-cover gas turbine engine component |
US11852035B2 (en) | 2019-05-07 | 2023-12-26 | Rtx Corporation | Multi-cover gas turbine engine component |
US11174737B2 (en) | 2019-06-12 | 2021-11-16 | Raytheon Technologies Corporation | Airfoil with cover for gas turbine engine |
US11248477B2 (en) | 2019-08-02 | 2022-02-15 | Raytheon Technologies Corporation | Hybridized airfoil for a gas turbine engine |
US11781436B2 (en) | 2019-08-02 | 2023-10-10 | Rtx Corporation | Hybridized airfoil for a gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
JP2016500136A (en) | 2016-01-07 |
JP6170159B2 (en) | 2017-07-26 |
US20180216626A1 (en) | 2018-08-02 |
WO2014099067A2 (en) | 2014-06-26 |
WO2014099067A3 (en) | 2014-08-21 |
EP2901023A2 (en) | 2015-08-05 |
EP2901023A4 (en) | 2015-11-04 |
EP2901023B1 (en) | 2019-10-30 |
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