US20020081205A1 - Reduced stress rotor blade and disk assembly - Google Patents
Reduced stress rotor blade and disk assembly Download PDFInfo
- Publication number
- US20020081205A1 US20020081205A1 US09/746,255 US74625500A US2002081205A1 US 20020081205 A1 US20020081205 A1 US 20020081205A1 US 74625500 A US74625500 A US 74625500A US 2002081205 A1 US2002081205 A1 US 2002081205A1
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- Prior art keywords
- root
- disk
- slot
- rotor assembly
- blade
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
-
- 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
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
-
- 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
- This invention relates to bladed rotor assemblies, and especially to bladed rotor assemblies for gas turbine engines.
- Bladed rotor assemblies are well known in the art, such as for compressors and turbines of gas turbine engines.
- each blade is often attached to the rotor disk by means of a root, integral with the radially innermost end of the blade.
- the root fits closely within a corresponding blade root slot extending generally axially through the disk rim, but at an angle to the true direction of the disk axis.
- the disk material disposed circumferentially between a pair of adjacent slots is often referred to as a disk lug.
- the blade root includes radially outwardly facing reaction surfaces that engage corresponding radially inwardly facing reaction surfaces of a blade root slot. During operation of the rotor, the blade loads are transferred into the disk and disk lugs through these engaged surfaces.
- a blade root extends from the front face to the rear face of the disk; and the engaged load reaction surfaces also extend from the front to the rear face of the disk (i.e. the full length of the slot). This is true of bladed disks having conventionally designed dovetail shaped roots and slots, as well as fir tree shaped roots and slots.
- a bladed rotor disk assembly includes a plurality of circumferentially spaced apart blade root slots extending through the disk at an angle to the disk axial direction and having radially inwardly facing load reaction surfaces extending continuously over less than the full the length of the slot in contact with a corresponding radially outwardly facing load reaction surface of a blade root disposed within the slot.
- load reaction surface it is meant the surfaces of the blade root and blade root slot that, during operation of the rotor, contact or engage each other to transfer the loads from the blade into the disk. When in contact these surfaces form a “load transfer interface”.
- the present invention eliminates what in the prior art would be portions of the load transfer interface adjacent the ends of the blade root slot, such that the loads over the remaining load transfer interface result in one or more of the following: a more symmetrical load distribution resulting in reduced torque loads on the disk lugs; reduced total loads on the disk lugs and blade roots; and, reduced maximum stress levels in the disk lugs and blade roots.
- a small area of each side of a slot adjacent an end of the slot and which faces what would normally be the low load portion of the root reaction surface is instead spaced from that low load portion such that there is a gap between the blade root and slot over that area.
- the blade and disk assembly may be considered conventional. The reaction loads over the now smaller load transfer interfaces on each side of the blade root are more balanced than without the gaps, and the maximum stress in the disk lugs is reduced.
- end portions of the conventional blade root that normally transfer relatively low loads into the disk lugs are removed, providing the benefit of reduced blade weight in addition to more balanced reaction loads over the remaining length of a smaller load transfer interface on each side of the blade root.
- Total reaction loads, stresses and/or torque on the disk lugs may thereby be reduced.
- Reduced torque loads means less twisting of the blade lugs, with correspondingly less twisting of the blades.
- FIG. 1 is an isometric rear view of a portion of a rotor assembly according to one embodiment of the present invention, with some of the blades removed to better show the blade root slots through the rim of the rotor disk.
- FIG. 2 is a sectional view taken along the line 2 - 2 of FIG. 1 through one of the rotor disk lugs, with the rotor disk axis being in the plane of the figure.
- FIG. 3 is a diagrammatic sectional view, taken along the line 3 - 3 of FIG. 2, illustrating the differences in reaction loads along the length of the slot as between a disk assembly of the prior art and a disk assembly according to one embodiment of the present invention.
- FIG. 4 is a view in the direction D of FIG. 3, parallel to the blade root slot length.
- FIGS. 5 and 6 are schematic views in the directions 5 - 5 and 6 - 6 , respectively, of FIG. 4 showing, for the embodiment of FIG. 1, the disk/blade load transfer interfaces along opposite sides of a blade root slot.
- FIG. 7 is a schematic view, taken in the direction 7 - 7 of FIG. 2, showing, for the embodiment of FIG. 1, the cross-sectional shape of the blade root and its general orientation relative to the front and rear disk surfaces and the blade platform.
- FIG. 8 is a sectional view of a rotor assembly, like the sectional view of FIG. 2, but showing a rotor assembly incorporating an alternate embodiment of the present invention.
- FIG. 9 is a simplified sectional view taken along the line 9 - 9 of FIG. 8.
- FIG. 10 is an isometric view in the direction S of FIG. 9 perpendicular to the rear face of the disk, with the blade removed.
- FIGS. 11 and 12 are schematic views in the directions 11 - 11 and 12 - 12 , respectively, of FIG. 4 showing, for the embodiment of FIG. 8, the disk/blade load transfer interfaces along opposite sides of a blade root slot.
- a gas turbine engine rotor assembly 100 incorporating an exemplary embodiment of the present invention includes a rotor disk 102 and a plurality of rotor blades 104 , only one of which is shown.
- Each blade comprises a root 106 , platform 108 , and airfoil 110 .
- the disk 102 has a rotational axis 111 , a rear face 112 , a front face 114 , and a rim 116 .
- a plurality of blade root slots 118 extends through the rim from the rear face to the front face in a direction D (FIG. 3). Each pair of adjacent slots defines a disk lug 120 therebetween.
- the root 106 of each blade is disposed within a respective one of the slots.
- each slot 118 extends in the direction D at an acute angle ⁇ to the direction of the disk axis 111 .
- this angle is between about 10° and 30°.
- ⁇ is 24° and, as best shown in FIG. 4, the blade roots 106 are of the well known “dovetail” shape, although the invention is not limited to use with blades having dovetail roots.
- the root of each blade has a pair of flat, radially outwardly facing load reaction surfaces 122 A, 122 B, one extending along each side of the root.
- the surfaces 122 A, 122 B abut corresponding flat, radially inwardly facing slot load reaction surfaces 124 A, 124 B, respectively.
- the interfaces formed by each of these pairs of contacting surfaces are hereinafter referred to as load transfer interfaces since, during operation of the rotor, the blade loads are transferred into the disk lugs across these interfaces.
- blade roots and disk slots, as well as the load transfer interfaces are the same length, which is generally the full length, L (FIG. 3), of the slot, as measured in the direction D of the slot.
- L the full length
- at least one of the blade root load reaction surfaces 122 A, 122 B, and preferably both, is less than the slot length. This is best seen in FIG. 3, wherein the blade root 106 , although fully within the slot 118 , has oppositely facing end surfaces 126 , 128 which are perpendicular to the slot direction D.
- FIG. 7 provides a radially outwardly looking view of the blade 104 , showing the orientation and position of the blade root 106 relative to the blade platform 108 and the disk front and rear faces 114 , 112 , respectively.
- FIGS. 3, 5 and 6 Reference is also made to FIGS. 3, 5 and 6 for an understanding of certain of the benefits of the present invention as compared to the prior art.
- the root load reaction surfaces 122 A, 122 B contact the slot load reaction surfaces 124 A, 124 B between the points Y and Z 1 , and W and X 1 , respectively.
- the blade root load reaction surfaces and slot load reaction surfaces extend the full length of the slot, such that over the radial extent (i.e. from R 1 to R 2 in FIG.
- the root end surfaces 126 , 128 are substantially in the planes of the disk rear and front faces 112 , 114 , respectively, as is generally the case with prior art rotor assemblies (i. e. the angle ⁇ is 0°, rather than being equal to ⁇ , as shown in FIG. 3).
- blade loads would be transferred into the disk lugs over the full length L of the slot from X 2 to W on one side of the slot and from Z 2 to Y on the other side.
- the magnitude of the reaction loads for such a prior art configuration along the lengths L of the respective blade root slot reaction surfaces are represented by the curves 132 , 134 , which were generated by a computer model of such a configuration.
- the curves 136 , 138 of FIG. 3 are generated by a computer model of the same rotor assembly modified according to the present invention (i.e. generally as shown in FIG. 1), and represent the magnitude of the reaction loads along the full lengths M (from X 1 to W) and N (from Z 1 to Y) of the blade root load reaction surfaces 122 A, 122 B, respectively.
- the perpendicular distance from the curves 132 , 136 to the line X 2 -W, and the perpendicular distance from the curves 134 , 138 to the line Z 2 -Y represent the magnitude of the reaction load.
- the benefits are primarily the result of lowering the weight of the blade by reducing the length of the blade root. That reduces the total load on the disk lugs and corresponding stress levels; and, by having a more balanced load over the length of the root, the stress concentrations are even further reduced.
- the reduced reaction load surface areas might negate these benefits; however, the loss of load reaction surface area is not particularly detrimental because the eliminated portions of the prior art reaction surfaces near the ends of the slots (the non-cross-hatched portions of FIGS. 5 and 6) were carrying only a relatively small portion of the total load per unit surface area, as compared to the average load per unit surface area over the full length of the slot.
- the blade root end surfaces 126 , 128 are perpendicular to the blade root load reaction surfaces 122 A, 122 B, this is not a requirement. It is preferred, however, that the blade root end surfaces be parallel to each other to maintain symmetry. Thus, a parallelogram cross-sectional shape (in the view of FIG. 3) with the blade root of any length less than the slot length L (in the direction D) may provide a benefit over the prior art by reducing blade weight.
- the angle ⁇ is between 0° and ⁇ .
- the blade root end surfaces 126 , 128 are preferably parallel, they need not be; and, thus, M does not need to equal N, although at least one of them must be less than L.
- the rotor assembly 200 includes a disk 202 and blades 204 , only one of which is shown.
- the disk axis is designated by the reference numeral 211 .
- the disk has front and rear parallel opposed faces 214 , 212 adjacent its rim 216 .
- the disk also has a plurality of circumferentially spaced apart blade root slots 218 defined by and between disk lugs 220 , and extending through the disk rim from the front face 212 to the rear face 214 . As in the previous embodiment, the slots 218 are cut at an angle to the disk axis 211 .
- Each blade 204 comprises a dovetail-shaped root 206 , platform 208 , and airfoil 210 .
- the blade roots extend the full length of their respective slots, whereby the root end surfaces 226 , 228 are substantially flush with respective end faces 212 , 214 of the disk, at least over the radial extent of the root load reaction surfaces.
- the lugs 220 on each side of a blade root 206 each have pockets 300 , 302 cut into opposite end faces 212 , 214 of the disk at the rim to cut back or remove material that would otherwise form a portion of a slot load reaction surface that engages a blade root load reaction surface.
- the root load reaction surface 222 A and the slot load reaction surface 224 A both extend from E 1 to F.
- the corresponding reaction surfaces 222 B and 224 B on the other side of the slot extend from G 1 to H.
- the pockets 300 , 302 create gaps 304 , 306 between each lug 220 and what are hereinafter referred to as extensions 308 (having a length from E 1 to E 2 ) and 310 (having a length from G 1 to G 2 ) of the blade root load reaction surfaces 222 A, 222 B, respectively.
- FIGS. 11 and 12 are analogous to FIGS. 5 and 6 of the previously described embodiment, and show the load transfer interfaces 230 A, 230 B, on each side of a slot in the embodiment of FIG. 8.
- L, M, and N represent the same lengths as in FIGS. 5 and 6. It is readily seen that both embodiments can result in the very same load transfer interfaces.
- the FIG. 1 embodiment accomplishes this by effectively shortening the length of the blade root; and the FIG. 8 embodiment does this by removing material from the slot surface to create a gap between a portion of the lug and the blade root. In each case the “removed” portion of the prior art load transfer interface was previously located where the prior art reaction loads were relatively low.
- gaps similar to the gaps 304 , 306 between the blade root and slot may be formed by removing a small amount of material from the blade root load reaction surfaces rather than from the disk lugs.
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Abstract
Description
- 1. Technical Field
- This invention relates to bladed rotor assemblies, and especially to bladed rotor assemblies for gas turbine engines.
- 2. Background Information
- Bladed rotor assemblies are well known in the art, such as for compressors and turbines of gas turbine engines. In such assemblies, each blade is often attached to the rotor disk by means of a root, integral with the radially innermost end of the blade. The root fits closely within a corresponding blade root slot extending generally axially through the disk rim, but at an angle to the true direction of the disk axis. The disk material disposed circumferentially between a pair of adjacent slots is often referred to as a disk lug. The blade root includes radially outwardly facing reaction surfaces that engage corresponding radially inwardly facing reaction surfaces of a blade root slot. During operation of the rotor, the blade loads are transferred into the disk and disk lugs through these engaged surfaces. Typically, a blade root extends from the front face to the rear face of the disk; and the engaged load reaction surfaces also extend from the front to the rear face of the disk (i.e. the full length of the slot). This is true of bladed disks having conventionally designed dovetail shaped roots and slots, as well as fir tree shaped roots and slots.
- It is generally desired to keep stresses within the disk and within the blades as low as possible to extend part life. In gas turbine engines designed for flight, it is also desired to minimize the weight of parts, such as disks and blades, consistent with efficient operation, long life and safety. Lighter weight blades also generate lower centrifugal forces and thus may reduce stresses within the disk.
- In accordance with the present invention, a bladed rotor disk assembly includes a plurality of circumferentially spaced apart blade root slots extending through the disk at an angle to the disk axial direction and having radially inwardly facing load reaction surfaces extending continuously over less than the full the length of the slot in contact with a corresponding radially outwardly facing load reaction surface of a blade root disposed within the slot.
- By “load reaction surface”, it is meant the surfaces of the blade root and blade root slot that, during operation of the rotor, contact or engage each other to transfer the loads from the blade into the disk. When in contact these surfaces form a “load transfer interface”.
- More specifically, the present invention eliminates what in the prior art would be portions of the load transfer interface adjacent the ends of the blade root slot, such that the loads over the remaining load transfer interface result in one or more of the following: a more symmetrical load distribution resulting in reduced torque loads on the disk lugs; reduced total loads on the disk lugs and blade roots; and, reduced maximum stress levels in the disk lugs and blade roots.
- One reason these benefits may occur is because, with conventional root and slot designs, when the blade root load reaction surface along a side of a blade root extends the full length of the slot, the highest and most concentrated reaction loads on that side of the slot occur adjacent one end of the slot, while relatively lower and less concentrated (i.e. more uniform) reaction loads on that same side of the slot occur adjacent the other end of the slot. Therefore, at the low, more uniform reaction load end of the slot, the disk lug material is carrying a relatively small portion of the blade load per square inch of load transfer interface, while at the high reaction load end the disk lug material is carrying a much larger portion of the blade load per square inch of load transfer interface. By eliminating load transfer interface area at the low load end of each side of a slot, the reaction loads over the remaining load transfer interface on each side of the slot becomes more balanced, and results in lower maximum stress.
- In one embodiment of the present invention a small area of each side of a slot adjacent an end of the slot and which faces what would normally be the low load portion of the root reaction surface is instead spaced from that low load portion such that there is a gap between the blade root and slot over that area. In all other respects, the blade and disk assembly may be considered conventional. The reaction loads over the now smaller load transfer interfaces on each side of the blade root are more balanced than without the gaps, and the maximum stress in the disk lugs is reduced.
- In another embodiment of the present invention, end portions of the conventional blade root that normally transfer relatively low loads into the disk lugs are removed, providing the benefit of reduced blade weight in addition to more balanced reaction loads over the remaining length of a smaller load transfer interface on each side of the blade root. Total reaction loads, stresses and/or torque on the disk lugs may thereby be reduced. Reduced torque loads means less twisting of the blade lugs, with correspondingly less twisting of the blades.
- The foregoing features and advantages of the present invention will become more apparent in light of the following detailed description of exemplary embodiments thereof as illustrated in the accompanying drawings.
- FIG. 1 is an isometric rear view of a portion of a rotor assembly according to one embodiment of the present invention, with some of the blades removed to better show the blade root slots through the rim of the rotor disk.
- FIG. 2 is a sectional view taken along the line2-2 of FIG. 1 through one of the rotor disk lugs, with the rotor disk axis being in the plane of the figure.
- FIG. 3 is a diagrammatic sectional view, taken along the line3-3 of FIG. 2, illustrating the differences in reaction loads along the length of the slot as between a disk assembly of the prior art and a disk assembly according to one embodiment of the present invention.
- FIG. 4 is a view in the direction D of FIG. 3, parallel to the blade root slot length.
- FIGS. 5 and 6 are schematic views in the directions5-5 and 6-6, respectively, of FIG. 4 showing, for the embodiment of FIG. 1, the disk/blade load transfer interfaces along opposite sides of a blade root slot.
- FIG. 7 is a schematic view, taken in the direction7-7 of FIG. 2, showing, for the embodiment of FIG. 1, the cross-sectional shape of the blade root and its general orientation relative to the front and rear disk surfaces and the blade platform.
- FIG. 8 is a sectional view of a rotor assembly, like the sectional view of FIG. 2, but showing a rotor assembly incorporating an alternate embodiment of the present invention.
- FIG. 9 is a simplified sectional view taken along the line9-9 of FIG. 8.
- FIG. 10 is an isometric view in the direction S of FIG. 9 perpendicular to the rear face of the disk, with the blade removed.
- FIGS. 11 and 12 are schematic views in the directions11-11 and 12-12, respectively, of FIG. 4 showing, for the embodiment of FIG. 8, the disk/blade load transfer interfaces along opposite sides of a blade root slot.
- Referring to FIGS. 1 and 2, a gas turbine
engine rotor assembly 100 incorporating an exemplary embodiment of the present invention includes arotor disk 102 and a plurality ofrotor blades 104, only one of which is shown. Each blade comprises aroot 106,platform 108, andairfoil 110. Thedisk 102 has arotational axis 111, arear face 112, afront face 114, and arim 116. A plurality ofblade root slots 118 extends through the rim from the rear face to the front face in a direction D (FIG. 3). Each pair of adjacent slots defines adisk lug 120 therebetween. Theroot 106 of each blade is disposed within a respective one of the slots. - Referring to FIG. 3, each
slot 118 extends in the direction D at an acute angle θ to the direction of thedisk axis 111. Generally, this angle is between about 10° and 30°. In this example θ is 24° and, as best shown in FIG. 4, theblade roots 106 are of the well known “dovetail” shape, although the invention is not limited to use with blades having dovetail roots. The root of each blade has a pair of flat, radially outwardly facingload reaction surfaces surfaces load reaction surfaces - In the prior art, blade roots and disk slots, as well as the load transfer interfaces, are the same length, which is generally the full length, L (FIG. 3), of the slot, as measured in the direction D of the slot. In accordance with the present invention, at least one of the blade root
load reaction surfaces blade root 106, although fully within theslot 118, has oppositely facingend surfaces load transfer interfaces load reaction surfaces blade 104, showing the orientation and position of theblade root 106 relative to theblade platform 108 and the disk front andrear faces - Reference is also made to FIGS. 3, 5 and6 for an understanding of certain of the benefits of the present invention as compared to the prior art. In the present invention, the root
load reaction surfaces load reaction surfaces root end surfaces front faces curves curves curves curves - Compare the “prior art” curves132, 134 to the
curves - In the foregoing embodiment, the benefits are primarily the result of lowering the weight of the blade by reducing the length of the blade root. That reduces the total load on the disk lugs and corresponding stress levels; and, by having a more balanced load over the length of the root, the stress concentrations are even further reduced. At first glance, it may appear that the reduced reaction load surface areas might negate these benefits; however, the loss of load reaction surface area is not particularly detrimental because the eliminated portions of the prior art reaction surfaces near the ends of the slots (the non-cross-hatched portions of FIGS. 5 and 6) were carrying only a relatively small portion of the total load per unit surface area, as compared to the average load per unit surface area over the full length of the slot.
- Although in the foregoing embodiment the blade root end surfaces126, 128 are perpendicular to the blade root load reaction surfaces 122A, 122B, this is not a requirement. It is preferred, however, that the blade root end surfaces be parallel to each other to maintain symmetry. Thus, a parallelogram cross-sectional shape (in the view of FIG. 3) with the blade root of any length less than the slot length L (in the direction D) may provide a benefit over the prior art by reducing blade weight. Preferably, the angle α is between 0° and θ. Although the blade root end surfaces 126, 128 are preferably parallel, they need not be; and, thus, M does not need to equal N, although at least one of them must be less than L.
- In accordance with another embodiment of the present invention, reference is made to FIGS. 8, 9 and10. The
rotor assembly 200 includes adisk 202 andblades 204, only one of which is shown. The disk axis is designated by thereference numeral 211. The disk has front and rear parallel opposed faces 214, 212 adjacent itsrim 216. The disk also has a plurality of circumferentially spaced apartblade root slots 218 defined by and between disk lugs 220, and extending through the disk rim from thefront face 212 to therear face 214. As in the previous embodiment, theslots 218 are cut at an angle to thedisk axis 211. Eachblade 204 comprises a dovetail-shapedroot 206,platform 208, andairfoil 210. In this embodiment, as is also the case in rotor assemblies of the prior art, the blade roots extend the full length of their respective slots, whereby the root end surfaces 226, 228 are substantially flush with respective end faces 212, 214 of the disk, at least over the radial extent of the root load reaction surfaces. - In accordance with this embodiment of the invention, the
lugs 220 on each side of ablade root 206 each have pockets 300, 302 cut into opposite end faces 212, 214 of the disk at the rim to cut back or remove material that would otherwise form a portion of a slot load reaction surface that engages a blade root load reaction surface. Thus, as shown in FIG. 9, wherein the cross-section through the blade root is shown crosshatched, the rootload reaction surface 222A and the slotload reaction surface 224A both extend from E1 to F. Similarly, the corresponding reaction surfaces 222B and 224B on the other side of the slot extend from G1 to H. Essentially, thepockets gaps lug 220 and what are hereinafter referred to as extensions 308 (having a length from E1 to E2) and 310 (having a length from G1 to G2) of the blade root load reaction surfaces 222A, 222B, respectively. - FIGS. 11 and 12 are analogous to FIGS. 5 and 6 of the previously described embodiment, and show the
load transfer interfaces curves - Although the invention has been described and illustrated with respect to exemplary embodiments thereof, it should be understood by those skilled in the art that the foregoing and various other changes, omissions and additions may be made without departing from the spirit and scope of the invention. For example, gaps similar to the
gaps
Claims (13)
Priority Applications (6)
Application Number | Priority Date | Filing Date | Title |
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US09/746,255 US6439851B1 (en) | 2000-12-21 | 2000-12-21 | Reduced stress rotor blade and disk assembly |
EP01310608A EP1219782B1 (en) | 2000-12-21 | 2001-12-19 | Bladed rotor assembly |
DE60138579T DE60138579D1 (en) | 2000-12-21 | 2001-12-19 | Bladed rotor assembly |
DE60128645T DE60128645T2 (en) | 2000-12-21 | 2001-12-19 | Rotor-blade-assembly |
EP07009913A EP1813771B1 (en) | 2000-12-21 | 2001-12-19 | Bladed rotor assembly |
JP2001386954A JP4101508B2 (en) | 2000-12-21 | 2001-12-20 | Rotor assembly |
Applications Claiming Priority (1)
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US09/746,255 US6439851B1 (en) | 2000-12-21 | 2000-12-21 | Reduced stress rotor blade and disk assembly |
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US20020081205A1 true US20020081205A1 (en) | 2002-06-27 |
US6439851B1 US6439851B1 (en) | 2002-08-27 |
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US09/746,255 Expired - Lifetime US6439851B1 (en) | 2000-12-21 | 2000-12-21 | Reduced stress rotor blade and disk assembly |
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US (1) | US6439851B1 (en) |
EP (2) | EP1219782B1 (en) |
JP (1) | JP4101508B2 (en) |
DE (2) | DE60138579D1 (en) |
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US20160177760A1 (en) * | 2014-12-18 | 2016-06-23 | General Electric Technology Gmbh | Gas turbine vane |
US20170226875A1 (en) * | 2014-09-30 | 2017-08-10 | Safran Aircraft Engines | Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk |
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GB0302116D0 (en) * | 2003-01-30 | 2003-03-05 | Rolls Royce Plc | A rotor |
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US20040126239A1 (en) * | 2002-12-26 | 2004-07-01 | Gautreau James Charles | Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge |
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US10260350B2 (en) * | 2014-09-05 | 2019-04-16 | United Technologies Corporation | Gas turbine engine airfoil structure |
US20170226875A1 (en) * | 2014-09-30 | 2017-08-10 | Safran Aircraft Engines | Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk |
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US10787915B2 (en) | 2014-09-30 | 2020-09-29 | Safran Aircraft Engines | Mobile vane for a turbine engine, comprising a lug engaging in a locking notch of a rotor disk |
US20160177760A1 (en) * | 2014-12-18 | 2016-06-23 | General Electric Technology Gmbh | Gas turbine vane |
US10221709B2 (en) * | 2014-12-18 | 2019-03-05 | Ansaldo Energia Switzerland AG | Gas turbine vane |
Also Published As
Publication number | Publication date |
---|---|
EP1219782A2 (en) | 2002-07-03 |
DE60128645T2 (en) | 2007-09-20 |
JP4101508B2 (en) | 2008-06-18 |
US6439851B1 (en) | 2002-08-27 |
EP1813771B1 (en) | 2009-04-29 |
EP1813771A2 (en) | 2007-08-01 |
DE60128645D1 (en) | 2007-07-12 |
DE60138579D1 (en) | 2009-06-10 |
EP1219782A3 (en) | 2003-10-08 |
EP1813771A3 (en) | 2008-02-20 |
EP1219782B1 (en) | 2007-05-30 |
JP2002201910A (en) | 2002-07-19 |
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