WO2002033224A1 - Fan blade compliant shim - Google Patents
Fan blade compliant shim Download PDFInfo
- Publication number
- WO2002033224A1 WO2002033224A1 PCT/US2001/032031 US0132031W WO0233224A1 WO 2002033224 A1 WO2002033224 A1 WO 2002033224A1 US 0132031 W US0132031 W US 0132031W WO 0233224 A1 WO0233224 A1 WO 0233224A1
- Authority
- WO
- WIPO (PCT)
- Prior art keywords
- shim
- assembly
- blade
- disk
- titanium
- Prior art date
Links
- 230000003647 oxidation Effects 0.000 claims abstract description 5
- 238000007254 oxidation reaction Methods 0.000 claims abstract description 5
- RTAQQCXQSZGOHL-UHFFFAOYSA-N Titanium Chemical compound [Ti] RTAQQCXQSZGOHL-UHFFFAOYSA-N 0.000 claims description 20
- 239000010936 titanium Substances 0.000 claims description 18
- 229910052719 titanium Inorganic materials 0.000 claims description 18
- 229910000531 Co alloy Inorganic materials 0.000 claims description 3
- 229910001069 Ti alloy Inorganic materials 0.000 claims description 3
- 239000010410 layer Substances 0.000 description 5
- 238000000034 method Methods 0.000 description 5
- 239000000463 material Substances 0.000 description 3
- 230000008569 process Effects 0.000 description 3
- 230000000977 initiatory effect Effects 0.000 description 2
- 230000007246 mechanism Effects 0.000 description 2
- 229910001092 metal group alloy Inorganic materials 0.000 description 2
- 241000499489 Castor canadensis Species 0.000 description 1
- 235000011779 Menyanthes trifoliata Nutrition 0.000 description 1
- 230000004075 alteration Effects 0.000 description 1
- 239000011248 coating agent Substances 0.000 description 1
- 238000000576 coating method Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000007689 inspection Methods 0.000 description 1
- 239000000314 lubricant Substances 0.000 description 1
- 230000013011 mating Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- CWQXQMHSOZUFJS-UHFFFAOYSA-N molybdenum disulfide Chemical compound S=[Mo]=S CWQXQMHSOZUFJS-UHFFFAOYSA-N 0.000 description 1
- 229910052982 molybdenum disulfide Inorganic materials 0.000 description 1
- 230000009467 reduction Effects 0.000 description 1
- 230000003252 repetitive effect Effects 0.000 description 1
- 230000000717 retained effect Effects 0.000 description 1
- 239000002356 single layer Substances 0.000 description 1
- 239000007787 solid Substances 0.000 description 1
- 238000012876 topography Methods 0.000 description 1
- 230000001052 transient effect Effects 0.000 description 1
Classifications
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
-
- 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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3092—Protective layers between blade root and rotor disc surfaces, e.g. anti-friction layers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05C—INDEXING SCHEME RELATING TO MATERIALS, MATERIAL PROPERTIES OR MATERIAL CHARACTERISTICS FOR MACHINES, ENGINES OR PUMPS OTHER THAN NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES
- F05C2201/00—Metals
- F05C2201/04—Heavy metals
- F05C2201/0433—Iron group; Ferrous alloys, e.g. steel
- F05C2201/0463—Cobalt
-
- 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
- F05D2230/90—Coating; Surface treatment
-
- 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
- F05D2240/50—Bearings
- F05D2240/54—Radial bearings
-
- 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
- F05D2250/00—Geometry
- F05D2250/70—Shape
- F05D2250/71—Shape curved
-
- 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
- F05D2260/30—Retaining components in desired mutual position
-
- 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
- F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
- F05D2300/611—Coating
Definitions
- This invention relates generally to gas turbine engines and in particular, to a compliant shim used between the dovetail root of a fan or compressor blade and the corresponding dovetail groove in a fan or compressor disk.
- Titanium alloys are used in aircraft and aircraft engines because of their good strength, low density and favorable environmental properties at low and moderate temperatures. If a particular design requires titanium pieces to rub against each other, the type of fatigue damage just outlined may occur.
- a titanium compressor disk also referred to as a rotor, or fan disk has an array of dovetail slots in its outer periphery.
- the dovetail base of a titanium compressor blade or fan blade fits into each dovetail slot of the disk.
- the dovetail of the blade is retained within the slot.
- centrifugal force induces the blade to move radially outward.
- the sides of the blade dovetail slide against the sloping sides of the dovetail slot of the disk, producing relative motion between the blade and the rotor disk.
- This sliding movement occurs between the disk and blade titanium pieces during transient operating conditions such as engine startup, power-up (takeoff), power-down and shutdown. With repeated cycles of operation, the sliding movement can affect surface topography and lead to a reduction in fatigue capability of the mating titanium pieces.
- normal and sliding forces exerted on the rotor in the vicinity of the dovetail slot can lead to galling, followed by the initiation and propagation of fatigue cracks in the disk. It is difficult to predict crack initiation or extent of damage as the number of engine cycles increase. Engine operators, such as the airlines, must therefore inspect the insides of the rotor dovetail slots frequently, which is a highly laborious process.
- One technique is to coat the contacting regions of the titanium pieces with a metallic alloy to protect the titanium parts from galling.
- the sliding contact between the two coated contacting regions is lubricated with a solid dry film lubricant containing primarily molybdenum disulfide, to further reduce friction.
- U.S. Patent Nos. 5,160,243 and 5,240,375 disclose a variety of single layer and multi-layer shims designed for mounting between the root of a titanium blade and its corresponding groove in a titanium rotor.
- the simplest of these shims is a U-shaped shim designed to be slide over the root of the fan blade, (see FIG. 3 of the '243 patent).
- a disadvantage to this type of shim are that it has a tendency to come lose during engine operation. Also, it does not entirely eliminate the fretting between the groove and the fan blade root.
- An object of the present invention is to provide an improved compliant shim for eliminating fretting between titanium components and a mechanism for holding such a shim in place during engine operation.
- the present invention meets this objective by providing compliant shim for use between the root of a gas turbine fan blade and a dovetail groove in a gas turbine rotor disk to reduce fretting therebetween.
- the compliant shim has first and second slots for engaging tabs extending from the fan blade root. The slots and tabs cooperate to hold the shim during engine operation.
- An oxidation layer covers the compliant shim and reduces fretting between the blade and the compliant layer.
- FIG. 1 is an exploded view of a rotor assembly contemplated by the present invention.
- FIG. 2 is a perspective view of a blade assembly having the compliant sleeve contemplated by the present invention.
- FIG. 3 is a perspective of the compliant sleeve contemplated by the present invention.
- FIG. 4 is a cross-sectional view taken along line 4-4 of FIG. 3.
- a fan assembly is generally denoted by the reference numeral 10.
- the assembly 10 includes a disk 12 having an annular web portion 14 and an outer periphery 16 having a plurality of dovetailed configured grooves 18 with radially outward facing base surfaces 20.
- the grooves 18 extend through the periphery 16 at an angle between the disk's 12 axial and tangential axes referred to as disk slot angle.
- Fan blades 30 are carried upon the outer periphery 16.
- Each blade 30 includes a radially upstanding airfoil portion 32 that extends from a leading edge 34 to a trailing edge 36.
- Each blade 30 also has a root portion 40 which is dovetail shaped to be received by one of the grooves 18.
- the root portion 40 has tabs 42, 44 that extend radially inward toward the base surface 20 to define a gap between the base surface 20 and an inner surface 41 of the root portion 40.
- a tab 46 adjacent the tab 44 extends further inward and abuts an axially facing surface of the outer periphery 16.
- the tab 46 is commonly referred to as a beaver tooth.
- the disk 12 and fan blade 30 are made from titanium or titanium alloys.
- the shim 50 is a thin, layered sheet formed for mounting in the gap between the base surface 20 and the inner surface 41.
- the shim 50 has a flat base 52 and two spaced apart walls 54, 64 that extend outward from the base 52.
- Each of the walls 54, 64 is curvilinear and has a first portion 56, 66 that curves away from each other, a second portion 58,68 that curves toward each other and a third portion 60, 70 that curves away from each other.
- the shim 40 extends from a first end 72 to a second end 76.
- the end 72 having a slot 74 for receiving tab 42 and the end 76 having a slot 78 for receiving tab 44.
- the blade 30 is mounted to the disk 12 by sliding a shim onto the root 40 and then inserting the shimmed blade into a dovetail slot in a manner familiar to those skilled in the art.
- the shim has an oxidation layer 80 over both it inner and outer surfaces.
- the layer 80 has a thickness in the range of .0002-.0003 inch on each side and is formed by heat treating the shim in an air atmosphere at 2075 °F for 14 to 16 minutes.
- the shim is preferably made of a cobalt alloy such as L605.
- a shim 50 is provided that prevent fretting between the fan blade root and its corresponding disk slot. Further, the shim 50 is slotted to engage tabs extending downward from the blade root which then hold the shim in place during the operation of the engine.
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Filters For Electric Vacuum Cleaners (AREA)
Abstract
Description
Claims
Priority Applications (3)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE60122550T DE60122550T2 (en) | 2000-10-17 | 2001-10-15 | SUSTAINABLE INTERMEDIATE PIECE FOR A FAN BOWL |
EP01977744A EP1327056B1 (en) | 2000-10-17 | 2001-10-15 | Fan blade compliant shim |
CA002426135A CA2426135C (en) | 2000-10-17 | 2001-10-15 | Fan blade compliant shim |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US09/690,216 US6431835B1 (en) | 2000-10-17 | 2000-10-17 | Fan blade compliant shim |
US09/690,216 | 2000-10-17 |
Publications (1)
Publication Number | Publication Date |
---|---|
WO2002033224A1 true WO2002033224A1 (en) | 2002-04-25 |
Family
ID=24771589
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
PCT/US2001/032031 WO2002033224A1 (en) | 2000-10-17 | 2001-10-15 | Fan blade compliant shim |
Country Status (7)
Country | Link |
---|---|
US (2) | US6431835B1 (en) |
EP (1) | EP1327056B1 (en) |
AT (1) | ATE337471T1 (en) |
CA (1) | CA2426135C (en) |
DE (1) | DE60122550T2 (en) |
TW (1) | TW567276B (en) |
WO (1) | WO2002033224A1 (en) |
Cited By (3)
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US10753213B2 (en) | 2017-05-03 | 2020-08-25 | MTU Aero Engines AG | Wear-resistant shield for a rotating blade of a gas turbine |
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US10753213B2 (en) | 2017-05-03 | 2020-08-25 | MTU Aero Engines AG | Wear-resistant shield for a rotating blade of a gas turbine |
Also Published As
Publication number | Publication date |
---|---|
TW567276B (en) | 2003-12-21 |
US6398499B1 (en) | 2002-06-04 |
DE60122550T2 (en) | 2007-09-20 |
EP1327056A1 (en) | 2003-07-16 |
US20020044870A1 (en) | 2002-04-18 |
EP1327056B1 (en) | 2006-08-23 |
CA2426135C (en) | 2008-01-08 |
DE60122550D1 (en) | 2006-10-05 |
ATE337471T1 (en) | 2006-09-15 |
US6431835B1 (en) | 2002-08-13 |
CA2426135A1 (en) | 2002-04-25 |
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