US20070056180A1 - Methods and apparatus for manufacturing components - Google Patents
Methods and apparatus for manufacturing components Download PDFInfo
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- US20070056180A1 US20070056180A1 US11/222,686 US22268605A US2007056180A1 US 20070056180 A1 US20070056180 A1 US 20070056180A1 US 22268605 A US22268605 A US 22268605A US 2007056180 A1 US2007056180 A1 US 2007056180A1
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- Prior art keywords
- fixture
- alignment member
- datum
- component
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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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/28—Supporting or mounting arrangements, e.g. for turbine casing
- F01D25/285—Temporary support structures, e.g. for testing, assembling, installing, repairing; Assembly methods using such structures
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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
- F05D2230/00—Manufacture
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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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
Definitions
- This invention relates generally to manufacturing components, and more specifically to methods and apparatus for aligning components for manufacture.
- Accurate manufacturing of gas turbine engine components may be a significant factor in determining both manufacturing timing and cost.
- accurate manufacturing of the blade may be a significant factors affecting an overall cost of fabrication of the gas turbine engine, as well as subsequent modifications, repairs, and inspections of the blade.
- at least some known gas turbine engine blades include a dovetail that typically requires an accurate machining process to create the dovetail profile and under platform surfaces.
- the blade may be coupled to a fixture that includes at least one surface that locates a plurality of datums on the dovetail and/or other portions of the blade. Similar portions of different gas turbine blades may sometimes be machined on the same machine. However, generally, different engine blades have different datums due to a difference in a size and/or shape of the blades. Accordingly, different engine blades generally require different locating surfaces on the fixture to accurately align the blades for machining. As a result, the entire fixture, or alternatively an alignment member or a locating surface used with the fixture, may have to be replaced to accommodate different blades. However, replacing alignment members or the entire fixture may be time consuming, and thereby increase engine manufacturing cycle times and fabrication costs.
- a method for aligning a first and a second component for manufacturing using an alignment member, wherein the first component includes at least one first datum and the second component includes at least one second datum.
- the method includes fixedly securing the alignment member to a fixture in a first orientation relative to the fixture, coupling the first component to the fixture such that the at least one first datum is aligned with a corresponding datum locator of a first datum nest of the alignment member, removing the first component from the fixture, repositioning the alignment member relative to the fixture from the first orientation to a second orientation relative to the fixture, fixedly securing the alignment member in the second orientation, and coupling the second component to the fixture such that the at least one second datum is aligned with a corresponding datum locator of a second datum nest of the alignment member.
- an alignment member for aligning a first component and a second component with a fixture to facilitate manufacturing the first and second components.
- the alignment member includes a first datum nest including at least one first datum locator configured to locate a corresponding datum of the first component when the alignment member is fixedly secured to the fixture in a first orientation relative to the fixture, and a second datum nest including at least one second datum locator configured to locate a corresponding datum of the second component when the alignment member is fixedly secured to the fixture in a second orientation relative to the fixture.
- an assembly for use in manufacturing a first component and a second component includes a fixture, and at least one alignment member for aligning the first and second components with the fixture.
- the alignment member includes a first datum nest including at least one first datum locator configured to locate a corresponding datum of the first component when the alignment member is fixedly secured to the fixture in a first orientation relative to the fixture, and a second datum nest including at least one second datum locator configured to locate a corresponding datum of the second component when the alignment member is fixedly secured to the fixture in a second orientation relative to the fixture.
- FIG. 1 is a perspective view of an exemplary gas turbine engine blade.
- FIG. 2 is a perspective view of another exemplary gas turbine engine blade.
- FIG. 3 is a perspective view of an exemplary embodiment of a fixture assembly for use in manufacturing a component, such as the gas turbine engine blades shown in FIGS. 1 and 2 .
- FIG. 4 is a perspective view of the exemplary fixture assembly shown in FIG. 3 .
- FIG. 5 is a perspective view of an exemplary embodiment of an alignment member for use with a fixture, such as the fixture shown in FIGS. 3 and 4 .
- FIG. 6 is a perspective view of the exemplary alignment member shown in FIG. 5 .
- FIG. 7 is a top plan view of the exemplary alignment member shown in FIGS. 5 and 6 in a first orientation relative to the fixture shown in FIGS. 3 and 4 .
- FIG. 8 is a top plan view of the exemplary alignment member shown in FIGS. 5 and 6 in a second orientation relative to the fixture shown in FIGS. 3 and 4 .
- the terms “manufacturing” and “manufacture” may include any process for shaping and/or evaluating a component, such as, but not limited to fabrication and/or inspection.
- machining may include any process used for shaping a component.
- processes used for shaping a component may include, but are not limited to including, turning, planing, milling, grinding, finishing, polishing, and/or cutting.
- shaping processes may include, but are not limited to including, processes performed by a machine, a machine tool, and/or a human being.
- the above examples are intended as exemplary only, and thus are not intended to limit in any way the definition and/or meaning of the terms “machining,” “machine,” and “machined”.
- inspection processes may include measurement by a machine, measurement by humans, visual inspection by a machine, and/or visual inspection by a human.
- inspection processes may include measurement by a machine, measurement by humans, visual inspection by a machine, and/or visual inspection by a human.
- the above examples are intended as exemplary only, and thus are not intended to limit in any way the definition and/or meaning of the terms “inspection” and “inspecting”.
- component may include any object that has been or may be manufactured.
- FIG. 1 is a perspective view of an exemplary engine blade 10 that may be used with a gas turbine engine (not shown).
- a plurality of turbine blades 10 form a high-pressure turbine rotor blade stage (not shown) within the gas turbine engine.
- Each blade 10 includes an airfoil 12 and an integral dovetail 14 that is used for mounting airfoil 12 to a rotor disk (not shown) in a known manner.
- blades 10 may extend radially outwardly from a disk (not shown), such that a plurality of blades 10 form a blisk (not shown).
- Each airfoil 12 includes a first contoured sidewall 16 and a second contoured sidewall 18 .
- First sidewall 16 is convex and defines a suction side of airfoil 12
- second sidewall 18 is concave and defines a pressure side of airfoil 12 .
- Sidewalls 16 and 18 are joined at a leading edge 20 and at an axially-spaced trailing edge 22 of airfoil 12 . More specifically, airfoil trailing edge 22 is spaced chordwise and downstream from airfoil leading edge 20 .
- First and second sidewalls 16 and 18 respectively, extend longitudinally or radially outward in span from a blade root 24 positioned adjacent dovetail 14 , to an airfoil tip 26 .
- airfoil tip 26 includes a tip shroud 28 extending radially outward therefrom in a direction away from airfoil 12 .
- a dovetail platform 30 is positioned at blade root 24 and extends radially outward from first and second sidewalls 16 and 18 , respectively.
- FIG. 2 is a perspective view of another exemplary engine blade 32 that may be used with a gas turbine engine (not shown).
- a plurality of turbine blades 32 form a high-pressure turbine rotor blade stage (not shown) within the gas turbine engine.
- Each blade 32 includes an airfoil 34 and an integral dovetail 36 that is used for mounting airfoil 34 to a rotor disk (not shown) in a known manner.
- blades 32 may extend radially outwardly from a disk (not shown), such that a plurality of blades 32 form a blisk (not shown).
- Each airfoil 34 includes a first contoured sidewall 38 and a second contoured sidewall 40 .
- First sidewall 38 is convex and defines a suction side of airfoil 34
- second sidewall 40 is concave and defines a pressure side of airfoil 34 .
- Sidewalls 38 and 40 are joined at a leading edge 42 and at an axially-spaced trailing edge 44 of airfoil 34 . More specifically, airfoil trailing edge 44 is spaced chordwise and downstream from airfoil leading edge 42 .
- First and second sidewalls 38 and 40 respectively, extend longitudinally or radially outward in span from a blade root 46 positioned adjacent dovetail 36 , to an airfoil tip 48 .
- airfoil tip 48 includes a tip shroud 50 extending radially outward therefrom in a direction away from airfoil 34 .
- a dovetail platform 52 is positioned at blade root 46 and extends radially outward from first and second sidewalls 38 and 40 , respectively.
- FIGS. 3 and 4 are perspective views of an exemplary embodiment of a fixture assembly 54 for use in manufacturing a component.
- fixture assembly 54 may be used to manufacture any component, for example components of any operable shape, size, configuration, and/or material(s), in the exemplary embodiment fixture assembly 54 is used in manufacturing engine blades 10 (shown FIG. 1 ) and 32 (shown in FIG. 2 ).
- engine blades 10 shown FIG. 1
- 32 shown in FIG. 2
- the specific size, shape, and/or configuration of fixture assembly 54 described and/or illustrated herein is exemplary only. Accordingly, the specific size, shape, and/or configuration of fixture assembly 54 generally, as well as portions thereof, may be selected to accommodate other components than engine blades 10 and 32 .
- Fixture assembly 54 includes a fixture 56 and at least one alignment member 58 for aligning blades 10 and 32 relative to fixture 56 .
- Blades 10 and/or 32 are separately coupled to fixture 56 for separate manufacture thereof.
- fixture assembly 54 may be positioned adjacent a machining tool (not shown) and/or an inspection tool (not shown) for machining and/or inspecting various surfaces of blades 10 and/or 32 .
- Blades 10 and 32 are coupled to fixture 56 in any suitable manner and using any suitable means.
- blades 10 and 32 are coupled to fixture 56 using a plurality of clamping mechanisms 60 .
- At least one clamping mechanism 60 includes a biasing mechanism (not shown), such as, but not limited to, a spring, to facilitate coupling blades 10 and 32 to fixture 56 .
- Alignment member 58 is secured to fixture 56 in any suitable manner and using any suitable means, such as, but not limited to, threaded fasteners.
- alignment member 58 aligns blades 10 and 32 with fixture 56 such that blades 10 and 32 are aligned with respect to a manufacturing tool and/or an inspection tool.
- FIG. 3 illustrates blade 10 coupled to, and aligned with, fixture 56 .
- FIG. 4 illustrates blade 32 coupled to, and aligned with, fixture 56 .
- FIGS. 5 and 6 are perspective views of an exemplary embodiment of alignment member 58 .
- FIGS. 7 and 8 are top plan views of alignment member 58 .
- Alignment member 58 includes a body 62 having a datum nest 64 for aligning blade 10 , and a datum nest 66 for aligning blade 32 .
- Datum nests 64 and 66 may each be located anywhere on alignment member 58 and may include any arrangement, configuration, size, and/or shape that facilitates aligning blades 10 and 32 , respectively.
- datum nests 64 and 66 may be located anywhere on alignment member body 62 relative to each other. Although only two datum nests 64 and 66 are illustrated, alignment member 58 may include any number of datum nests for aligning any number of different components with fixture 56 .
- alignment member body 62 includes a surface 68 that includes datum nest 64 , and an opposing surface 70 that includes datum nest 66 .
- Datum nest 64 includes a plurality of datum locators 72 , 74 , and 76 on datum nest surface 68 for locating a plurality of datums 78 , 80 , and 82 , respectively, on blade 10 . Although three datum locators 72 , 74 , and 76 are illustrated, datum nest 64 may include any number of datum locators for locating any number of datums on blade 10 . Moreover, datums 78 , 80 , and 82 may be located anywhere on blade 10 . In the exemplary embodiment, datum 78 is located on blade tip shroud 28 , datum 80 is located on blade dovetail platform 30 , and datum 82 is located on blade root 14 .
- Datum nest 66 includes a plurality of datum locators 84 , 86 , and 88 on datum nest surface 70 for locating a plurality of datums 90 , 92 , and 94 , respectively, on blade 32 . Although three datum locators 84 , 86 , and 88 are illustrated, datum nest 66 may include any number of datum locators for locating any number of datums on blade 32 . Moreover, datums 90 , 92 , and 94 may be located anywhere on blade 32 . In the exemplary embodiment, datum 90 is located on blade tip shroud 50 , datum 92 is located on blade dovetail platform 52 , and datum 94 is located on blade root 36 .
- alignment member 58 can be changed to accommodate the particular component being manufactured. More specifically, and as shown in FIGS. 3 and 7 , to manufacture blades 10 and 32 using fixture 56 , alignment member 58 is fixedly secured to fixture 56 in an orientation 96 relative to fixture 56 that facilitates manufacturing blade 10 . (Alternatively, blade 32 is manufactured before blade 10 .) To facilitate positioning alignment member 58 in orientation 96 , in the exemplary embodiment alignment member 58 includes at least one slot 98 (shown in FIG. 5 ) defined therein for receiving an extension (not shown) extending from fixture 56 . The extension is sized for insertion in slot 98 .
- alignment member 58 may include any number of slots 98 for receiving any number of extensions.
- fixture 56 includes at least one slot (not shown) defined therein for receiving an extension (not shown) extending outwardly from alignment member 58 to facilitate positioning alignment member 58 in orientation 96 .
- the extension is sized for insertion in the slot.
- fixture 56 may include any number of slots for receiving any number of extensions.
- alignment member 58 includes at least one slot 102 (shown in FIG. 5 ) defined therein for receiving an extension (not shown) extending from fixture 56 .
- the extension is sized for insertion in slot 102 .
- alignment member 58 may include any number of slots 102 for receiving any number of extensions.
- fixture 56 includes at least one slot (not shown) defined therein for receiving an extension (not shown) extending outwardly from alignment member 58 to facilitate positioning alignment member 58 in orientation 100 .
- the extension is sized for insertion in the slot.
- fixture 56 may include any number of slots for receiving any number of extensions.
- blade 32 is coupled to fixture 56 such that datum 90 is aligned with datum locator 84 , datum 92 is aligned with datum locator 86 , and datum 94 is aligned with datum locator 88 .
- a manufacturing process can then performed on blade 32 .
- alignment member 58 can be used to align both blades 10 and 32 by moving alignment member 58 between orientations 96 and 100 . Alignment member 58 therefore does not need to be replaced with another alignment member and/or fixture when switching between manufacturing processes performed on blades 10 and 32 . Accordingly, alignment member 58 may facilitate reducing a cycle time of manufacturing blades 10 and 32 , thereby possibly reducing an overall cost of manufacturing blades 10 and 32 . Moreover, slots 98 and 102 of alignment member 58 may facilitate accurate positioning of alignment member 58 in orientations 96 and 100 , respectively, in less time, thereby possibly increasing repeatability and further reducing a cycle time of manufacture of blades 10 and 32 . Furthermore, because a separate alignment member and/or fixture may not be required to align blades 10 and 32 , alignment member 58 may increase an amount of available storage and/or work space adjacent a machine that includes fixture assembly 54 .
- assemblies, members, and methods described and/or illustrated herein are described and/or illustrated with respect to gas turbine engine components, and more specifically a rotor blade for a gas turbine engine, practice of the assemblies, members, and methods described and/or illustrated herein is not limited to engine blades, nor gas turbine engine components generally. Rather, the assemblies, members, and methods described and/or illustrated herein are applicable to any component and/or any manufacturing process.
- assemblies, members, and methods are described and/or illustrated herein in detail.
- the assemblies, members, and methods are not limited to the specific embodiments described herein, but rather, components of each member and components of each assembly, as well as steps of each method, may be utilized independently and separately from other components and steps described herein.
- Each component, and each method step can also be used in combination with other components and/or method steps.
- the articles “a”, “an”, “the” and “said” are intended to mean that there are one or more of the element(s)/component(s)/etc.
- the terms “comprising”, “including” and “having” are intended to be inclusive and mean that there may be additional element(s)/component(s)/etc. other than the listed element(s)/component(s)/etc.
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Abstract
Description
- This invention relates generally to manufacturing components, and more specifically to methods and apparatus for aligning components for manufacture.
- Accurate manufacturing of gas turbine engine components may be a significant factor in determining both manufacturing timing and cost. Specifically, when the component is a gas turbine engine blade, accurate manufacturing of the blade may be a significant factors affecting an overall cost of fabrication of the gas turbine engine, as well as subsequent modifications, repairs, and inspections of the blade. For example, at least some known gas turbine engine blades include a dovetail that typically requires an accurate machining process to create the dovetail profile and under platform surfaces.
- To align the dovetail for machining, the blade may be coupled to a fixture that includes at least one surface that locates a plurality of datums on the dovetail and/or other portions of the blade. Similar portions of different gas turbine blades may sometimes be machined on the same machine. However, generally, different engine blades have different datums due to a difference in a size and/or shape of the blades. Accordingly, different engine blades generally require different locating surfaces on the fixture to accurately align the blades for machining. As a result, the entire fixture, or alternatively an alignment member or a locating surface used with the fixture, may have to be replaced to accommodate different blades. However, replacing alignment members or the entire fixture may be time consuming, and thereby increase engine manufacturing cycle times and fabrication costs.
- In one aspect, a method is provided for aligning a first and a second component for manufacturing using an alignment member, wherein the first component includes at least one first datum and the second component includes at least one second datum. The method includes fixedly securing the alignment member to a fixture in a first orientation relative to the fixture, coupling the first component to the fixture such that the at least one first datum is aligned with a corresponding datum locator of a first datum nest of the alignment member, removing the first component from the fixture, repositioning the alignment member relative to the fixture from the first orientation to a second orientation relative to the fixture, fixedly securing the alignment member in the second orientation, and coupling the second component to the fixture such that the at least one second datum is aligned with a corresponding datum locator of a second datum nest of the alignment member.
- In another aspect, an alignment member is provided for aligning a first component and a second component with a fixture to facilitate manufacturing the first and second components. The alignment member includes a first datum nest including at least one first datum locator configured to locate a corresponding datum of the first component when the alignment member is fixedly secured to the fixture in a first orientation relative to the fixture, and a second datum nest including at least one second datum locator configured to locate a corresponding datum of the second component when the alignment member is fixedly secured to the fixture in a second orientation relative to the fixture.
- In even another aspect, an assembly for use in manufacturing a first component and a second component includes a fixture, and at least one alignment member for aligning the first and second components with the fixture. The alignment member includes a first datum nest including at least one first datum locator configured to locate a corresponding datum of the first component when the alignment member is fixedly secured to the fixture in a first orientation relative to the fixture, and a second datum nest including at least one second datum locator configured to locate a corresponding datum of the second component when the alignment member is fixedly secured to the fixture in a second orientation relative to the fixture.
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FIG. 1 is a perspective view of an exemplary gas turbine engine blade. -
FIG. 2 is a perspective view of another exemplary gas turbine engine blade. -
FIG. 3 is a perspective view of an exemplary embodiment of a fixture assembly for use in manufacturing a component, such as the gas turbine engine blades shown inFIGS. 1 and 2 . -
FIG. 4 is a perspective view of the exemplary fixture assembly shown inFIG. 3 . -
FIG. 5 is a perspective view of an exemplary embodiment of an alignment member for use with a fixture, such as the fixture shown inFIGS. 3 and 4 . -
FIG. 6 is a perspective view of the exemplary alignment member shown inFIG. 5 . -
FIG. 7 is a top plan view of the exemplary alignment member shown inFIGS. 5 and 6 in a first orientation relative to the fixture shown inFIGS. 3 and 4 . -
FIG. 8 is a top plan view of the exemplary alignment member shown inFIGS. 5 and 6 in a second orientation relative to the fixture shown inFIGS. 3 and 4 . - As used herein, the terms “manufacturing” and “manufacture” may include any process for shaping and/or evaluating a component, such as, but not limited to fabrication and/or inspection. As used herein the terms “machining,” “machine,” and “machined” may include any process used for shaping a component. For example, processes used for shaping a component may include, but are not limited to including, turning, planing, milling, grinding, finishing, polishing, and/or cutting. In addition, and for example, shaping processes may include, but are not limited to including, processes performed by a machine, a machine tool, and/or a human being. The above examples are intended as exemplary only, and thus are not intended to limit in any way the definition and/or meaning of the terms “machining,” “machine,” and “machined”.
- As used herein, the terms “inspection” and “inspecting” may include any inspection process. For example, inspection processes may include measurement by a machine, measurement by humans, visual inspection by a machine, and/or visual inspection by a human. The above examples are intended as exemplary only, and thus are not intended to limit in any way the definition and/or meaning of the terms “inspection” and “inspecting”. In addition, as used herein the term “component” may include any object that has been or may be manufactured.
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FIG. 1 is a perspective view of anexemplary engine blade 10 that may be used with a gas turbine engine (not shown). In some embodiments, a plurality ofturbine blades 10 form a high-pressure turbine rotor blade stage (not shown) within the gas turbine engine. Eachblade 10 includes anairfoil 12 and anintegral dovetail 14 that is used for mountingairfoil 12 to a rotor disk (not shown) in a known manner. Alternatively,blades 10 may extend radially outwardly from a disk (not shown), such that a plurality ofblades 10 form a blisk (not shown). - Each
airfoil 12 includes a first contouredsidewall 16 and a second contouredsidewall 18.First sidewall 16 is convex and defines a suction side ofairfoil 12, andsecond sidewall 18 is concave and defines a pressure side ofairfoil 12.Sidewalls edge 20 and at an axially-spacedtrailing edge 22 ofairfoil 12. More specifically, airfoiltrailing edge 22 is spaced chordwise and downstream fromairfoil leading edge 20. First andsecond sidewalls blade root 24 positionedadjacent dovetail 14, to anairfoil tip 26. In the exemplary embodiment,airfoil tip 26 includes atip shroud 28 extending radially outward therefrom in a direction away fromairfoil 12. Adovetail platform 30 is positioned atblade root 24 and extends radially outward from first andsecond sidewalls -
FIG. 2 is a perspective view of anotherexemplary engine blade 32 that may be used with a gas turbine engine (not shown). In some embodiments, a plurality ofturbine blades 32 form a high-pressure turbine rotor blade stage (not shown) within the gas turbine engine. Eachblade 32 includes anairfoil 34 and anintegral dovetail 36 that is used for mountingairfoil 34 to a rotor disk (not shown) in a known manner. Alternatively,blades 32 may extend radially outwardly from a disk (not shown), such that a plurality ofblades 32 form a blisk (not shown). - Each
airfoil 34 includes a first contouredsidewall 38 and a second contouredsidewall 40.First sidewall 38 is convex and defines a suction side ofairfoil 34, andsecond sidewall 40 is concave and defines a pressure side ofairfoil 34.Sidewalls edge 42 and at an axially-spacedtrailing edge 44 ofairfoil 34. More specifically, airfoiltrailing edge 44 is spaced chordwise and downstream fromairfoil leading edge 42. First andsecond sidewalls blade root 46 positionedadjacent dovetail 36, to anairfoil tip 48. In the exemplary embodiment,airfoil tip 48 includes atip shroud 50 extending radially outward therefrom in a direction away fromairfoil 34. Adovetail platform 52 is positioned atblade root 46 and extends radially outward from first andsecond sidewalls -
FIGS. 3 and 4 are perspective views of an exemplary embodiment of afixture assembly 54 for use in manufacturing a component. Althoughfixture assembly 54 may be used to manufacture any component, for example components of any operable shape, size, configuration, and/or material(s), in the exemplaryembodiment fixture assembly 54 is used in manufacturing engine blades 10 (shownFIG. 1 ) and 32 (shown inFIG. 2 ). Of course, it should be appreciated that the specific size, shape, and/or configuration offixture assembly 54 described and/or illustrated herein is exemplary only. Accordingly, the specific size, shape, and/or configuration offixture assembly 54 generally, as well as portions thereof, may be selected to accommodate other components thanengine blades -
Fixture assembly 54 includes afixture 56 and at least onealignment member 58 for aligningblades fixture 56.Blades 10 and/or 32 are separately coupled tofixture 56 for separate manufacture thereof. For example,fixture assembly 54 may be positioned adjacent a machining tool (not shown) and/or an inspection tool (not shown) for machining and/or inspecting various surfaces ofblades 10 and/or 32.Blades fixture 56 in any suitable manner and using any suitable means. In the exemplary embodiment,blades fixture 56 using a plurality of clampingmechanisms 60. In some embodiments, at least oneclamping mechanism 60 includes a biasing mechanism (not shown), such as, but not limited to, a spring, to facilitatecoupling blades fixture 56.Alignment member 58 is secured tofixture 56 in any suitable manner and using any suitable means, such as, but not limited to, threaded fasteners. Generally,alignment member 58 alignsblades fixture 56 such thatblades FIG. 3 illustratesblade 10 coupled to, and aligned with,fixture 56.FIG. 4 illustratesblade 32 coupled to, and aligned with,fixture 56. -
FIGS. 5 and 6 are perspective views of an exemplary embodiment ofalignment member 58.FIGS. 7 and 8 are top plan views ofalignment member 58.Alignment member 58 includes abody 62 having adatum nest 64 for aligningblade 10, and adatum nest 66 for aligningblade 32.Datum nests alignment member 58 and may include any arrangement, configuration, size, and/or shape that facilitates aligningblades datum nests alignment member body 62 relative to each other. Although only twodatum nests alignment member 58 may include any number of datum nests for aligning any number of different components withfixture 56. In the exemplary embodiment,alignment member body 62 includes asurface 68 that includesdatum nest 64, and an opposingsurface 70 that includesdatum nest 66. -
Datum nest 64 includes a plurality ofdatum locators datum nest surface 68 for locating a plurality ofdatums blade 10. Although threedatum locators datum nest 64 may include any number of datum locators for locating any number of datums onblade 10. Moreover, datums 78, 80, and 82 may be located anywhere onblade 10. In the exemplary embodiment,datum 78 is located onblade tip shroud 28,datum 80 is located onblade dovetail platform 30, anddatum 82 is located onblade root 14. -
Datum nest 66 includes a plurality ofdatum locators datum nest surface 70 for locating a plurality ofdatums blade 32. Although threedatum locators datum nest 66 may include any number of datum locators for locating any number of datums onblade 32. Moreover, datums 90, 92, and 94 may be located anywhere onblade 32. In the exemplary embodiment,datum 90 is located onblade tip shroud 50,datum 92 is located onblade dovetail platform 52, anddatum 94 is located onblade root 36. - To manufacture different components, such as
blades alignment member 58 can be changed to accommodate the particular component being manufactured. More specifically, and as shown inFIGS. 3 and 7 , to manufactureblades fixture 56,alignment member 58 is fixedly secured tofixture 56 in anorientation 96 relative tofixture 56 that facilitatesmanufacturing blade 10. (Alternatively,blade 32 is manufactured beforeblade 10.) To facilitatepositioning alignment member 58 inorientation 96, in the exemplaryembodiment alignment member 58 includes at least one slot 98 (shown inFIG. 5 ) defined therein for receiving an extension (not shown) extending fromfixture 56. The extension is sized for insertion inslot 98. Although twoslots 98 are illustrated,alignment member 58 may include any number ofslots 98 for receiving any number of extensions. Moreover, in some embodiments,fixture 56 includes at least one slot (not shown) defined therein for receiving an extension (not shown) extending outwardly fromalignment member 58 to facilitatepositioning alignment member 58 inorientation 96. The extension is sized for insertion in the slot. Moreover,fixture 56 may include any number of slots for receiving any number of extensions. Oncealignment member 58 is fixedly secured inorientation 96,blade 10 is coupled tofixture 56 such thatdatum 78 is aligned withdatum locator 72,datum 80 is aligned withdatum locator 74, anddatum 82 is aligned withdatum locator 76. A manufacturing process can then be performed onblade 10. - To manufacture
blade 32,blade 10 is removed fromfixture 56 andalignment member 58 is repositioned relative tofixture 56 fromorientation 96 to anorientation 100, shown inFIGS. 4 and 8 , relative tofixture 56 that facilitatesmanufacturing blade 32.Alignment member 58 is then fixedly secured tofixture 56 inorientation 100.Alignment member 58 can be repositioned using any movement, for example in any direction and by any amount, to be repositioned betweenorientations datum nests alignment member 58. In the exemplary embodiment,alignment member 58 is rotated about 180° about a centrallongitudinal axis 104 or acentral axis 106 ofalignment member 58 to move betweenorientations - To facilitate
positioning alignment member 58 inorientation 100, in the exemplaryembodiment alignment member 58 includes at least one slot 102 (shown inFIG. 5 ) defined therein for receiving an extension (not shown) extending fromfixture 56. The extension is sized for insertion inslot 102. Although twoslots 102 are illustrated,alignment member 58 may include any number ofslots 102 for receiving any number of extensions. Moreover, in some embodiments,fixture 56 includes at least one slot (not shown) defined therein for receiving an extension (not shown) extending outwardly fromalignment member 58 to facilitatepositioning alignment member 58 inorientation 100. The extension is sized for insertion in the slot. Moreover,fixture 56 may include any number of slots for receiving any number of extensions. Oncealignment member 58 is fixedly secured inorientation 100,blade 32 is coupled tofixture 56 such thatdatum 90 is aligned withdatum locator 84,datum 92 is aligned withdatum locator 86, anddatum 94 is aligned withdatum locator 88. A manufacturing process can then performed onblade 32. - As described above, because
alignment member 58 includesdatum nests alignment member 58 can be used to align bothblades alignment member 58 betweenorientations Alignment member 58 therefore does not need to be replaced with another alignment member and/or fixture when switching between manufacturing processes performed onblades alignment member 58 may facilitate reducing a cycle time ofmanufacturing blades manufacturing blades slots alignment member 58 may facilitate accurate positioning ofalignment member 58 inorientations blades blades alignment member 58 may increase an amount of available storage and/or work space adjacent a machine that includesfixture assembly 54. - Although the assemblies, members, and methods described and/or illustrated herein are described and/or illustrated with respect to gas turbine engine components, and more specifically a rotor blade for a gas turbine engine, practice of the assemblies, members, and methods described and/or illustrated herein is not limited to engine blades, nor gas turbine engine components generally. Rather, the assemblies, members, and methods described and/or illustrated herein are applicable to any component and/or any manufacturing process.
- Exemplary embodiments of assemblies, members, and methods are described and/or illustrated herein in detail. The assemblies, members, and methods are not limited to the specific embodiments described herein, but rather, components of each member and components of each assembly, as well as steps of each method, may be utilized independently and separately from other components and steps described herein. Each component, and each method step, can also be used in combination with other components and/or method steps.
- When introducing elements/components/etc. of the assemblies, members, and methods described and/or illustrated herein, the articles “a”, “an”, “the” and “said” are intended to mean that there are one or more of the element(s)/component(s)/etc. The terms “comprising”, “including” and “having” are intended to be inclusive and mean that there may be additional element(s)/component(s)/etc. other than the listed element(s)/component(s)/etc.
- While the invention has been described in terms of various specific embodiments, those skilled in the art will recognize that the invention can be practiced with modification within the spirit and scope of the claims.
Claims (20)
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US11/222,686 US7178255B1 (en) | 2005-09-09 | 2005-09-09 | Methods and apparatus for manufacturing components |
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US11/222,686 US7178255B1 (en) | 2005-09-09 | 2005-09-09 | Methods and apparatus for manufacturing components |
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US20070056180A1 true US20070056180A1 (en) | 2007-03-15 |
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US8931184B1 (en) * | 2012-05-21 | 2015-01-13 | General Electric Company | Method for dimensionally inspecting a component of a gas turbine system |
WO2013180916A1 (en) * | 2012-05-30 | 2013-12-05 | United Technologies Corporation | Assembly fixture for a stator vane assembly |
US20140223709A1 (en) | 2013-02-08 | 2014-08-14 | General Electric Company | Turbomachine rotor blade milling machine system and method of field repairing a turbomachine rotor blade |
US9778650B2 (en) * | 2013-12-11 | 2017-10-03 | Honda Motor Co., Ltd. | Apparatus, system and method for kitting and automation assembly |
EP2998063B1 (en) * | 2014-09-16 | 2019-03-13 | Ansaldo Energia Switzerland AG | Tool for measuring geometrical parameters of a blade or vane in a turbomachine |
US10125634B2 (en) | 2015-12-10 | 2018-11-13 | General Electric Company | Combustor assembly alignment and securement systems |
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