US3867069A - Alternate root turbine blading - Google Patents
Alternate root turbine blading Download PDFInfo
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- US3867069A US3867069A US357436A US35743673A US3867069A US 3867069 A US3867069 A US 3867069A US 357436 A US357436 A US 357436A US 35743673 A US35743673 A US 35743673A US 3867069 A US3867069 A US 3867069A
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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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
Definitions
- ABSTRACT A rotor for an axial flow elastic fluid turbine apparatus.
- the rotor has a rotating shaft member having at least a first and a second rooted blade secured to the shaft. Each rooted blade has a platform portion thereon.
- a rootless blade, having a platform portion thereon, is disposed intermediate between each pair of first and the second rooted blades.
- the underside surface of each of the platforms on the rootless blades directly abuts the shaft member, with the platforms of the rooted blades contacting the platform of the rootless blades to radially secure the rootless blades in position.
- a protruding pin member diposed on the underside surfaces of each of the rootless blades engages a circumferential slot in the shaft member to axially secure the rootless blades.
- the invention relates to axial flow elastic fluid turbine apparatus, and in particular, to a bladed rotor structure utilized in the turbine apparatus.
- a plurality of blade members are secured to a rotating shaft member by engaging a root portion of each blade with a substantially axial groove disposed in the rotor shaft.
- a common blade root configuration is the fir tree type, side entry blade root.
- the fir tree style root is a generally triangular shaped root, having a plurality of protrusions producing a serrated edge that extends from the base of the root toward the tip thereof.
- the root is usually curved and is received by the correspondingly curved-groove disposed in the shaft member in such a way that the tip of the substantially triangular root is the radially innermost portion of the turbine blade.
- the invention discloses a rotor for an axial flow elastic fluid turbine apparatus having a generally cylindrical rotating shaft member having a plurality of generally axial grooves spaced a predetermined circumferential distance about the periphery of the shaft member.
- a first and second rooted blade are disposed in adjacent shaft grooves.
- the root portion of each blade is comprised of a generally cylindrical knob portion and a rectanguloid neck portion connected thereto.
- the cylindrical knob poriton is the radially innermost portion of the blade root and has a large fillet forming the transition between the substantially cylindrical knob and the rectanguloid neck portion.
- Both the first and the second rooted blades have a platform portion thereon. Disposed intermediate the adjacent rooted blades is a rootless blade having a platform portion thereon. The rootless blade is disposed immediately adjacent to and directly abutting the rotor shaft. The rootless blade is radially secured in position by contact between the platforms on rooted blade and the platform of the rootless blade.
- a pin extending from the underside surface of the rootless blade platform engages a circumferential slot disposed about the periphery of the rotor shaft member to axially secure the rootless blade in position.
- An object of the invention is to provide a blading arrangement for an axial flow elastic fluid turbine apparatus wherein each blade has a stronger, more efficient root configuration.
- a still further object of the invention is to provide a bladeroot configuration requiring half the number of axial grooves than have been heretofore required, thereby.
- FIG. 1 is a perspective view of a portion of a bladed rotor structure embodying the teachings of the present invention.
- FIG. 2 is a side elevational view of a portion of the bladed rotor structure shown in FIG. 1.
- FIG. 1 there is shown a perspective view of a fragment of a rotor structure 10 that is part of an axial flow elastic fluid turbine apparatus (not shown) while FIG. 2 illustrates an elevational' view of the rotor 10.
- the blade structure described by the teachings of this invention can be utilized on any blade array for an axial flow elastic fluid turbine apparatus.
- the rotor structure 10 includes a portion of the rotor shaft 12. As shown in FIGS. 1 and 2, the rotor shaft 12 has a row of grooves 14 which extend axially about the periphery of the rotor shaft 12 and which extend radially inward a predetermined distance 16 from the surface of the rotor shaft 12.
- the grooves 12 are spaced a predetermined circumferential distance 18 from each other and are similar to each other in shape and size.
- the grooves have a generally cylindrical knob slot 20 and a generally rectanguloid slot 22, with a large fillet transition slot 24 between the cylindrical knob slot and the rectanguloid slot 22'.
- the portion of the shaft member between adjacent grooves 12 is known to those skilled in the prior art as the steeple," hereinafter referred to by reference numeral 28.
- a first rooted blade 30 and a second rooted blade 32 are attached to the rotor shaft 12.
- the first rooted blade 30 has a root portion 34, a platform portion 36 and an airfoil portion 38 extending radially outward from the platform portion 36.
- the second rooted blade has a root portion 34, a platform portion 36' and an airfoil portion 38 extending radially outward from the platform portion 36.
- a generous fillet portion 44 and 44 is disposed between the knob portions 40 and 40' and the rectanguloid neck portions 42 and 42.
- the root portions 34 and 34 of the first rooted blade 30 and the second rooted blade 32, respectively, are axially inserted into adjacent axial grooves 14 as illustrated in the drawing.
- the lateral protrusions provide the platform portions 36 and 36' with a circumferential dimension 50 and 50' that is greater than the circumferential dimension 52 and 52 ofthe rectanguloid neck portions 42 and 42 on the first rooted blade 30 and the second rooted blade 32 respectively.
- the airfoil portions 38 and 38 are connected to a circumferential shroud 54 by suitable means illustrated in FIG. 1 as a rivet 56.
- a slot 58 extends circumferentially about the shaft 12.
- a rootless blade 70 having a platform portion 72 thereon, is disposed intermediate between the first rooted blade 30 and the second rooted blade 32.
- the underside of the platform portion 72 of the rootless blade 70 abuts directly against the steeple portion 28 of the rotor shaft 12.
- the platform portion 72 of the rootless blade 70 has a first lateral protrusion 74 and a second lateral protrusion 76 thereon.
- the exterior surface of the lateral protrusion 74 of the rootless blade 70 is contacted by the underside surface of the lateral protrusion 48 of the second rooted blade 32.
- the exterior surface of the lateral protrusion 76 of the rootless blade 70 is contacted by the underside surface of the lateral protrusion 46 of the first rooted blade 30.
- the contact interface between the rootless blade 70 and the rooted blades 30 and 32 is illustrated by reference numbers 80 and 82 respectively.
- the platform portions 36 and 36' of the rooted blades 30 and 32 respectively contact the platform portion 72 of the rootlcss blade 70 to radially secure the rootless blade 70 di rectly against the rotor shaft 12.
- the arrangement disposing the rootless blade 70 intermediate between the first rooted blade 30 and the second rooted blade 32 is repeated until alternate rooted and rootless blades are disposed about the entire circumference of the rotor shaft 12.
- the rotor embodied by the teachings of this invention differs from the prior art, and especially the aforementioned Bernales patent, in that the rootless blade in this invention directly abuts against the steeple portion 28 of the rotor shaft 12, while in the aforementioned Bernales patent, the base of the rootless blades abut a lateral extension of the rooted blades. These lateral extensions from the rooted blades in turn abut the steeple of the rotor shaft.
- a pin 84 is disposed on the underside surface of the rootless blade and engages the slot 58 extending circumferentially about the periphery of the rotor shaft 12. The engagement of the pin 84 in the slot 58 in the rotor shaft 12 axially secures the rootless blade 70 in position.
- root configuration 34 and 34' utilized by the rooted blades 30 and 32 in this invention is a simple and easy to fabricate configuration, which will be less expensive to manufacture than are the fir tree roots utilized in the prior art.
- the large fillets 44 and 44' eliminates stress concentrations which were observed with the fir tree type root, thus preventing premature failure of the blade root caused by excessive stresses on the root. Also, since there are one half the number of rooted blades than were required in the prior art, fabrication of the rotor and the broaching time required to fabricate the axial grooves 14 is significantly reduced, thus reducing manufacturing expense.
- the rooted blades 30 and 32 and the rootless blade 70 each have a different point of fixity, that is, a different point of attachment to the shaft 12.
- the differing points of fixity between the rooted blades 30 and 32 and the rootless blade 70 insures that a different natural frequency of vibration will exist in the rooted blades 30 and 32 than in the rootless blade 70.
- an improved rotor structure utilizing at least a first and a second rooted blade, with an intermediate rootless blade disposed therebetween, provides an effective blade damper and also provides for ease of fabrication of a rotor memberQ
- the rootless blade is secured radially by contact between the platform portion of the rooted blade with the platform portion of the rootless blade.
- the rootless blade is secured in the axial direction b y a pin and slot arrangement.
- a rotor for axial flow elastic fluid turbine apparatus comprising:
- a shaft member having a plurality of axial grooves disposed circumferentially about the periphery thereof and having a surface area thereon, said grooves being a predetermined circumferential distance from each other,
- a first rooted blade disposed in one of said plurality of axial grooves, said first rooted blade having a platform portion thereon;
- a rootless blade having a platform portion thereon, said platform portion having an underside surface thereon, said underside surface of said platform portion of said rootless blade directly abutting said surface area on said shaft member, said platform portion of said first rooted blade and said platform portion of said second rooted blade contacting said platform portion of said rootless blade to radially secure said rootless blade in position against said shaft member and,
- said means for damping relative motion between said rooted blades and said rootless blade comprising said contacting platform portions adapted so that relative motion between said rooted blades and said rootless blade generates a friction force therebetween to dampen said relative motion.
- the rotor of claim 1 further comprising means for axially securing said rootless blade to said shaft member, said axial securing means comprising a slot disposed circumferentially about the periphery of said shaft, and,
- transition portion disposed radially between said knob portion and said neck portion, said transition portion being disposed so as to prevent stresses from concentrating adjacent roots as said roots radially secure said rooted blades to said shaft, said knob portion and said transition portion being completely disposed radially beneath the surface of said shaft, a predetermined portion of said neck 6 being disposed radially beneath said surface of said shaft.
- said platform portion of said second rooted blade has a laterally extending protrusion
- said platform portion of said rootless blade has a first lateral protrusion thereon and a second lateral protrusion thereon, the underside surface of said platform portion of said rootless blade and the underside portions of said lateral protrusions of said rootless blade directly abut said rotor shaft, said lateral protrusion of said first rooted blade contacting said first lateral protrusion of said rootless blade, said lateral protrusion of said second rooted blade contacting said second lateral protrusion of rootless blade, contact between said rootless blade and said first rooted blade and said second rooted blade radially secures said platform portion of said rootless blade in the abutting relationship with said rotor.
- said lateral protrusions on said rootless blade each have a smooth surface on the radially outer side thereof
- a rotor for an axial flow, elastic fluid turbine apparatus comprising:
- a shaft member having a plurality of axial grooves extending radially into said shaft and arranged circumferentially about the periphery thereof, said grooves defining a predetermined surface area of said shaft therebetween,
- each root being disposed in adjacent axial grooves, each root having a predetermined circumferential dimension at the point on said root radially adjacent said surface of said shaft,
- said first and said second rooted blades each having a platform portion thereon spaced radially outward from said roots, said platforms each having a first and a second lateral protrusion thereon, the circumferential dimension on each blade between edges of said lateral protrusions being greater than said predetermined circumferential dimension of said root, said protrusions being spaced radially away from said shaft surface, each protrusion having a smooth underside surface thereon,
- said first protrusion on said first rooted blade and said second protrusion on said second rooted blade each circumferentially overlapping a portion of said surface area between said first and said second rooted blades
- a rootless blade disposed between said first and said second rooted blades, said rootless blade having a platform portion having a first and a second lateral protrusion thereon, the greatest circumferential dimension of said rootless blade being disposed across said lateral protrusions,
- said platform portion of said rootless blade having a smooth underside surface thereon, said lateral protrusions of said rootless balde having smooth radially outer surfaces thereon, said underside surface of said rootless blade platform directly abutting against said surface of said shaft between first and said second rooted blades,
- said smooth, radially outer surface of said first protrusion of said rootless blade being radially beneath and overlapped by said smooth underside surface of said first lateral protrusion on said first rooted blade
- said smooth radially outer surface of said second protrusion on said rootless blade being radially beneath and overlapped by said smooth, underside surface of said second lateral protrusion on said second rooted blade
- said rooted blades and said rootless blade being adapted so that relative motion between said rootless and said rooted blades generates a friction force between said smooth overlapping, contacting and abrading surfaces to dampen said relative mo tion between said rooted blades and said rootless blade.
- root portion which radially secures said first and said second rooted blades to said shaft comprises a substantailly cylindrical knob portion; a substantially rectanguloid neck portion connected to said knob portion, and,
- knob portion being the radially innermost portion of said root when said root is disposed in one of said adjacent axial grooves
- said predetermined dimension of said root being taken at a point on said neck portion adjacent said surface of said shaft
- transition portion between said knob and said neck being disposed so as to prevent stress concentration adjacent said root as said root radially secures said blade to said rotor.
- said rootless blade is attached to said shaft by said rooted blades at a second point of fixity
- said first point of fixity being radially inward on said shaft from said second point of fixity
- said rotor further comprising means for axially securing said rootless blades to said shaft, said means comprising a pin member radially extending form said underside surface of said rootless blade, and
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Abstract
A rotor for an axial flow elastic fluid turbine apparatus. The rotor has a rotating shaft member having at least a first and a second rooted blade secured to the shaft. Each rooted blade has a platform portion thereon. A rootless blade, having a platform portion thereon, is disposed intermediate between each pair of first and the second rooted blades. The underside surface of each of the platforms on the rootless blades directly abuts the shaft member, with the platforms of the rooted blades contacting the platform of the rootless blades to radially secure the rootless blades in position. In addition, a protruding pin member diposed on the underside surfaces of each of the rootless blades engages a circumferential slot in the shaft member to axially secure the rootless blades.
Description
United States Patent [191 Bussell [4 1 Feb. 18, 1975 ALTERNATE ROOT TURBINE BLADING [21] Appl. No.: 357,436
Switzerland 416/220 Switzerland 416/220 Primary ExaminerEverette A. Powell, Jr. Attorney, Agent, or Firm-C. H. Telfer [5 7] ABSTRACT A rotor for an axial flow elastic fluid turbine apparatus. The rotor has a rotating shaft member having at least a first and a second rooted blade secured to the shaft. Each rooted blade has a platform portion thereon. A rootless blade, having a platform portion thereon, is disposed intermediate between each pair of first and the second rooted blades. The underside surface of each of the platforms on the rootless blades directly abuts the shaft member, with the platforms of the rooted blades contacting the platform of the rootless blades to radially secure the rootless blades in position. In addition, a protruding pin member diposed on the underside surfaces of each of the rootless blades engages a circumferential slot in the shaft member to axially secure the rootless blades.
8 Claims, 2 Drawing Figures PATENTED 5 SHEET 10? 2 ALTERNATE ROOT TURBINE BLADING BACKGROUND OF THE INVENTION 1. Field of the'lnvention:
The invention relates to axial flow elastic fluid turbine apparatus, and in particular, to a bladed rotor structure utilized in the turbine apparatus.
2. Description of the Prior Art:
In an axial flow elastic fluid turbine apparatus, a plurality of blade members are secured to a rotating shaft member by engaging a root portion of each blade with a substantially axial groove disposed in the rotor shaft. A common blade root configuration is the fir tree type, side entry blade root. The fir tree style root is a generally triangular shaped root, having a plurality of protrusions producing a serrated edge that extends from the base of the root toward the tip thereof. The root is usually curved and is received by the correspondingly curved-groove disposed in the shaft member in such a way that the tip of the substantially triangular root is the radially innermost portion of the turbine blade.
Due to the complexity of the root shape, and the number of roots generally required around a given shaft circumference, geometry dictates that the fir tree root utilize an extremely small fillet portion between the root body and each serration, or tang, which extends from the root body. However, stress concentrations tend to form around these fillets which impose a high stress load on the blade root.
In addition to formation of high stress concentrations, it has been shown that the usual fir tree root configuration does not provide universal contact between all surfaces of the tangs and the rotor body. Thus, even under intermediate centrifugal force loading, universal contact between all surfaces of the tangs and the rotor body does not occur.
It is obvious, therefore, that high stress concentra tions and the almost total reliance for radial restraint of the blades on the outer surfaces of the tangs leads to ex cessive stress and premature failure of the fir tree type root. Also, machining of the plurality of grooves that accommodate the fir tree roots is a time-eonsuming and expensive process.
In the prior art, attempts have been made to eliminate half the number of grooves required by disposing a plurality of rooted blades and inserting therebetween an intermediate rootless blade having a keyed portion thereon. The keyed portion of the intermediate blade engages a corresponding keyed portion on the platform of the rooted blades while the base of the intcrmediate blade rests upon a lateral protrusion from the rooted blades. An example of the prior art utilizing this technique is disclosed in the U.S. Pat. No. 3,702,202, issued to Bernales, and assigned to the as signee of the present invention. However, the complex shape of the blade root was not changed, and the stress concentrations found when utilizing the fir tree type root still remain.
SUMMARY OF THE INVENTION The invention discloses a rotor for an axial flow elastic fluid turbine apparatus having a generally cylindrical rotating shaft member having a plurality of generally axial grooves spaced a predetermined circumferential distance about the periphery of the shaft member. A first and second rooted blade are disposed in adjacent shaft grooves. The root portion of each blade is comprised of a generally cylindrical knob portion and a rectanguloid neck portion connected thereto. The cylindrical knob poriton is the radially innermost portion of the blade root and has a large fillet forming the transition between the substantially cylindrical knob and the rectanguloid neck portion.
Both the first and the second rooted blades have a platform portion thereon. Disposed intermediate the adjacent rooted blades is a rootless blade having a platform portion thereon. The rootless blade is disposed immediately adjacent to and directly abutting the rotor shaft. The rootless blade is radially secured in position by contact between the platforms on rooted blade and the platform of the rootless blade.
A pin extending from the underside surface of the rootless blade platform engages a circumferential slot disposed about the periphery of the rotor shaft member to axially secure the rootless blade in position.
An object of the invention is to provide a blading arrangement for an axial flow elastic fluid turbine apparatus wherein each blade has a stronger, more efficient root configuration.
In addition, it is advantageous, and therefore a further object of the invention, to provide a blading arrangement for an axial flow elastic fluidturbine apparatus that provides an improved blade damper thereby improving the efficiency of the apparatus. A still further object of the invention is to provide a bladeroot configuration requiring half the number of axial grooves than have been heretofore required, thereby.
making the tooling operation on the grooves simpler and less expensive.
BRIEF DESCRIPTION OF THE DRAWINGS The invention will be more fully understood from the.
following detailed description of an illustrative embodiment taken in connection with the accompanying drawings, in which:
FIG. 1 is a perspective view of a portion of a bladed rotor structure embodying the teachings of the present invention; and
FIG. 2 is a side elevational view of a portion of the bladed rotor structure shown in FIG. 1.
DESCRIPTION OF THE PREFERRED EMBODIMENT Throughout the following description, similar reference characters refer to similar elements of the drawings.
Referring to the drawings in FIG. 1, there is shown a perspective view of a fragment of a rotor structure 10 that is part of an axial flow elastic fluid turbine apparatus (not shown) while FIG. 2 illustrates an elevational' view of the rotor 10. The blade structure described by the teachings of this invention can be utilized on any blade array for an axial flow elastic fluid turbine apparatus.
The rotor structure 10 includes a portion of the rotor shaft 12. As shown in FIGS. 1 and 2, the rotor shaft 12 has a row of grooves 14 which extend axially about the periphery of the rotor shaft 12 and which extend radially inward a predetermined distance 16 from the surface of the rotor shaft 12. The grooves 12 are spaced a predetermined circumferential distance 18 from each other and are similar to each other in shape and size. The grooves have a generally cylindrical knob slot 20 and a generally rectanguloid slot 22, with a large fillet transition slot 24 between the cylindrical knob slot and the rectanguloid slot 22'.
The portion of the shaft member between adjacent grooves 12 is known to those skilled in the prior art as the steeple," hereinafter referred to by reference numeral 28.
A first rooted blade 30 and a second rooted blade 32 are attached to the rotor shaft 12. The first rooted blade 30 has a root portion 34, a platform portion 36 and an airfoil portion 38 extending radially outward from the platform portion 36. The second rooted blade has a root portion 34, a platform portion 36' and an airfoil portion 38 extending radially outward from the platform portion 36.
The root portions 34 and 34' of the first rooted blade and the second rooted blade, respectively, each have a cylindrical knob portion 40 and 40 connected to a rectanguloid portion 42 and 42. A generous fillet portion 44 and 44 is disposed between the knob portions 40 and 40' and the rectanguloid neck portions 42 and 42.
The root portions 34 and 34 of the first rooted blade 30 and the second rooted blade 32, respectively, are axially inserted into adjacent axial grooves 14 as illustrated in the drawing.
The platform portions 36 and 36 of the ifrst rooted blade 30 and the second rooted blade 32, respectively, have a first lateral protrusion 46 and 46 and a second lateral protrusion 48 and 48. The lateral protrusions provide the platform portions 36 and 36' with a circumferential dimension 50 and 50' that is greater than the circumferential dimension 52 and 52 ofthe rectanguloid neck portions 42 and 42 on the first rooted blade 30 and the second rooted blade 32 respectively.
The airfoil portions 38 and 38 are connected to a circumferential shroud 54 by suitable means illustrated in FIG. 1 as a rivet 56. A slot 58 extends circumferentially about the shaft 12.
A rootless blade 70, having a platform portion 72 thereon, is disposed intermediate between the first rooted blade 30 and the second rooted blade 32. The underside of the platform portion 72 of the rootless blade 70 abuts directly against the steeple portion 28 of the rotor shaft 12.
The platform portion 72 of the rootless blade 70 has a first lateral protrusion 74 and a second lateral protrusion 76 thereon.
The exterior surface of the lateral protrusion 74 of the rootless blade 70 is contacted by the underside surface of the lateral protrusion 48 of the second rooted blade 32. The exterior surface of the lateral protrusion 76 of the rootless blade 70 is contacted by the underside surface of the lateral protrusion 46 of the first rooted blade 30.
The contact interface between the rootless blade 70 and the rooted blades 30 and 32 is illustrated by reference numbers 80 and 82 respectively. The platform portions 36 and 36' of the rooted blades 30 and 32 respectively contact the platform portion 72 of the rootlcss blade 70 to radially secure the rootless blade 70 di rectly against the rotor shaft 12.
The arrangement disposing the rootless blade 70 intermediate between the first rooted blade 30 and the second rooted blade 32 is repeated until alternate rooted and rootless blades are disposed about the entire circumference of the rotor shaft 12.
The rotor embodied by the teachings of this invention differs from the prior art, and especially the aforementioned Bernales patent, in that the rootless blade in this invention directly abuts against the steeple portion 28 of the rotor shaft 12, while in the aforementioned Bernales patent, the base of the rootless blades abut a lateral extension of the rooted blades. These lateral extensions from the rooted blades in turn abut the steeple of the rotor shaft.
A pin 84 is disposed on the underside surface of the rootless blade and engages the slot 58 extending circumferentially about the periphery of the rotor shaft 12. The engagement of the pin 84 in the slot 58 in the rotor shaft 12 axially secures the rootless blade 70 in position.
It is apparent that the root configuration 34 and 34' utilized by the rooted blades 30 and 32 in this invention is a simple and easy to fabricate configuration, which will be less expensive to manufacture than are the fir tree roots utilized in the prior art.
In addition, the large fillets 44 and 44' eliminates stress concentrations which were observed with the fir tree type root, thus preventing premature failure of the blade root caused by excessive stresses on the root. Also, since there are one half the number of rooted blades than were required in the prior art, fabrication of the rotor and the broaching time required to fabricate the axial grooves 14 is significantly reduced, thus reducing manufacturing expense.
By utilization of the alternate root blading embodied by the teachings of this invention, it is possible to provide an effective blade damper for the blades, thus improving the efficiency of the turbine apparatus.
As is well known to those skilled in the art, the rooted blades 30 and 32 and the rootless blade 70, each have a different point of fixity, that is, a different point of attachment to the shaft 12. The differing points of fixity between the rooted blades 30 and 32 and the rootless blade 70 insures that a different natural frequency of vibration will exist in the rooted blades 30 and 32 than in the rootless blade 70.
Since this is so, whe vibrations are engendered within the rooted blades 30 and 32 and the rootless blade 70, such vibrations emanating, for example, from the impingement of elastic fluid on the blades at the nozzles of the turbine apparatus, relative motion between the rooted and the rootless blades will occur. If all of the blades on a turbine had the same point of fixity, it is evident that no relative motion will be observed between the blades, since all blades will have the same natural frequency of vibration. However, since the points of fixity of the rooted blades 30 and 32 and the rootless blade 70 differ, relative motion will exist between the rooted blades 30 and 32 and the rootless blade 70.
When vibratory forces are imposed upon the rooted blades 30 and 32 and the rootless blade 70, and the relative motion between the blades has been initiated, the interaction of the rootless blade 70 with the rooted blades 30 and 32, as illustrated at interfaces and 82, will result in heat energy being developed by the abrasion of the rootless blade 70 against the rooted blades 30 and 32. The heat energy generated by the abrasion between the rooted blades 30 and 32 and the rootless blade 70 will absorb the vibratory energy in the blades, thus providing an effective damper for the blades that was unavailable with the prior art blades.
It is thus seen, that an improved rotor structure, utilizing at least a first and a second rooted blade, with an intermediate rootless blade disposed therebetween, provides an effective blade damper and also provides for ease of fabrication of a rotor memberQThe rootless blade is secured radially by contact between the platform portion of the rooted blade with the platform portion of the rootless blade. The rootless blade is secured in the axial direction b y a pin and slot arrangement.
l claim as my invention:
1. A rotor for axial flow elastic fluid turbine apparatus comprising:
a shaft member having a plurality of axial grooves disposed circumferentially about the periphery thereof and having a surface area thereon, said grooves being a predetermined circumferential distance from each other,
a first rooted blade disposed in one of said plurality of axial grooves, said first rooted blade having a platform portion thereon;
a second rooted blade disposed in an adjacent axial groove, said second rooted blade having a platform portion thereon,;
a rootless blade having a platform portion thereon, said platform portion having an underside surface thereon, said underside surface of said platform portion of said rootless blade directly abutting said surface area on said shaft member, said platform portion of said first rooted blade and said platform portion of said second rooted blade contacting said platform portion of said rootless blade to radially secure said rootless blade in position against said shaft member and,
means for damping relative motion between said rooted blades and said rootless blade, said means comprising said contacting platform portions adapted so that relative motion between said rooted blades and said rootless blade generates a friction force therebetween to dampen said relative motion.
2. The rotor of claim 1, further comprising means for axially securing said rootless blade to said shaft member, said axial securing means comprising a slot disposed circumferentially about the periphery of said shaft, and,
a pin member extending radially form said underside surface of said rootless blade, said direct abutment between said underside surface of said platform portion of said rootless blade and said surface area on said shaft permitting said radially extending pin member to engage said circumferential slot to axially secure said rootless blade to said shaft.
3. The rotor of claim 1, wherein said first and said second rooted blade each has a root member comprising a radially innermost substantially cylindrical knob portion,
a substantially rectanguloid neck portion connected to said knob portion, and
a transition portion disposed radially between said knob portion and said neck portion, said transition portion being disposed so as to prevent stresses from concentrating adjacent roots as said roots radially secure said rooted blades to said shaft, said knob portion and said transition portion being completely disposed radially beneath the surface of said shaft, a predetermined portion of said neck 6 being disposed radially beneath said surface of said shaft.
4. The rotor of claim 1, wherein said platform poriton of said first rooted blade has a laterally extending protrusion thereon,
said platform portion of said second rooted blade has a laterally extending protrusion; and,
said platform portion of said rootless blade has a first lateral protrusion thereon and a second lateral protrusion thereon, the underside surface of said platform portion of said rootless blade and the underside portions of said lateral protrusions of said rootless blade directly abut said rotor shaft, said lateral protrusion of said first rooted blade contacting said first lateral protrusion of said rootless blade, said lateral protrusion of said second rooted blade contacting said second lateral protrusion of rootless blade, contact between said rootless blade and said first rooted blade and said second rooted blade radially secures said platform portion of said rootless blade in the abutting relationship with said rotor.
5. The rotor of claim 4, wherein said lateral protrusions on said first and said second rooted blades each have a smooth surface on the underside thereof,
said lateral protrusions on said rootless blade each have a smooth surface on the radially outer side thereof,
said smooth underside surfaces of said lateral protrusions of said first and said second rooted blades overlapping and contacting against said smooth radially outer surfaces on said lateral protrusions of said rootless blade,
said relative motion between said rooted and rootless blades generating said friction force along said overlapped and contacted smooth surfaces on said platforms of said rooted blades and said rootless blade to dampen said relative motion therebetween.
6. A rotor for an axial flow, elastic fluid turbine apparatus comprising:
a shaft member having a plurality of axial grooves extending radially into said shaft and arranged circumferentially about the periphery thereof, said grooves defining a predetermined surface area of said shaft therebetween,
a first and a second blade having a root thereon, each root being disposed in adjacent axial grooves, each root having a predetermined circumferential dimension at the point on said root radially adjacent said surface of said shaft,
said first and said second rooted blades each having a platform portion thereon spaced radially outward from said roots, said platforms each having a first and a second lateral protrusion thereon, the circumferential dimension on each blade between edges of said lateral protrusions being greater than said predetermined circumferential dimension of said root, said protrusions being spaced radially away from said shaft surface, each protrusion having a smooth underside surface thereon,
said first protrusion on said first rooted blade and said second protrusion on said second rooted blade each circumferentially overlapping a portion of said surface area between said first and said second rooted blades, and,
a rootless blade disposed between said first and said second rooted blades, said rootless blade having a platform portion having a first and a second lateral protrusion thereon, the greatest circumferential dimension of said rootless blade being disposed across said lateral protrusions,
said platform portion of said rootless blade having a smooth underside surface thereon, said lateral protrusions of said rootless balde having smooth radially outer surfaces thereon, said underside surface of said rootless blade platform directly abutting against said surface of said shaft between first and said second rooted blades,
said smooth, radially outer surface of said first protrusion of said rootless blade being radially beneath and overlapped by said smooth underside surface of said first lateral protrusion on said first rooted blade, said smooth radially outer surface of said second protrusion on said rootless blade being radially beneath and overlapped by said smooth, underside surface of said second lateral protrusion on said second rooted blade,
the smooth underside surfaces of said lateral protrusions of said rooted blades overlapping, contacting and abrading against the radially outer surfaces of said lateral protrusions of said rootless blade to radially secure said rootless blade to said rotor,
said rooted blades and said rootless blade being adapted so that relative motion between said rootless and said rooted blades generates a friction force between said smooth overlapping, contacting and abrading surfaces to dampen said relative mo tion between said rooted blades and said rootless blade.
7. The rotor of claim 6, wherein said root portion which radially secures said first and said second rooted blades to said shaft comprises a substantailly cylindrical knob portion; a substantially rectanguloid neck portion connected to said knob portion, and,
a transition portion disposed radially between said knob portion and said neck portion,
said knob portion being the radially innermost portion of said root when said root is disposed in one of said adjacent axial grooves,
said predetermined dimension of said root being taken at a point on said neck portion adjacent said surface of said shaft,
said transition portion between said knob and said neck being disposed so as to prevent stress concentration adjacent said root as said root radially secures said blade to said rotor.
8. The rotor of claim 7, wherein said rooted blades are attached to said shaft by said root portions thereof at a first point of fixity therebetween, and,
said rootless blade is attached to said shaft by said rooted blades at a second point of fixity,
said first point of fixity being radially inward on said shaft from said second point of fixity,
said difference in points of fixity for said rooted blades on said rootless blade permittingrelative motion to occur between said rooted blades and said rootless blade,
said rotor further comprising means for axially securing said rootless blades to said shaft, said means comprising a pin member radially extending form said underside surface of said rootless blade, and
a slot disposed circumferentially about said shaft surface,
said direct abutment of said underside surface of said platform of said rootless blade against said surface of said shaft permitting said pin member to be radially inserted and radially engage said slot to axially secure said rootless blade to said shaft.
Claims (8)
1. A rotor for axial flow elastic fluid turbine apparatus comprising: a shaft member having a plurality of axial grooves disposed circumferentially about the periphery thereof and having a surface area thereon, said grooves being a predetermined circumferential distance from each other, a first rooted blade disposed in one of said plurality of axial grooves, said first rooted blade having a platform portion thereon; a second rooted blade disposed in an adjacent axial groove, said second rooted blade having a platform portion thereon,; a rootless blade having a platform portion thereon, said platform portion having an underside sUrface thereon, said underside surface of said platform portion of said rootless blade directly abutting said surface area on said shaft member, said platform portion of said first rooted blade and said platform portion of said second rooted blade contacting said platform portion of said rootless blade to radially secure said rootless blade in position against said shaft member and, means for damping relative motion between said rooted blades and said rootless blade, said means comprising said contacting platform portions adapted so that relative motion between said rooted blades and said rootless blade generates a friction force therebetween to dampen said relative motion.
2. The rotor of claim 1, further comprising means for axially securing said rootless blade to said shaft member, said axial securing means comprising a slot disposed circumferentially about the periphery of said shaft, and, a pin member extending radially form said underside surface of said rootless blade, said direct abutment between said underside surface of said platform portion of said rootless blade and said surface area on shaft permitting said radially extending pin member to engage said circumferential slot to axially secure said rootless blade to said shaft.
3. The rotor of claim 1, wherein said first and said second rooted blade each has a root member comprising a radially innermost substantially cylindrical knob portion, a substantially rectanguloid neck portion connected to said knob portion, and a transition portion disposed radially between said knob portion and said neck portion, said transition portion being disposed so as to prevent stresses from concentrating adjacent roots as said roots radially secure said rooted blades to said shaft, said knob portion and said transition portion being completely disposed radially beneath the surface of said shaft, a predetermined portion of said neck being disposed radially beneath said surface of said shaft.
4. The rotor of claim 1, wherein said platform poriton of said first rooted blade has a laterally extending protrusion thereon, said platform portion of said second rooted blade has a laterally extending protrusion; and, said platform portion of said rootless blade has a first lateral protrusion thereon and a second lateral protrusion thereon, the underside surface of said platform portion of said rootless blade and the underside portions of said lateral protrusions of said rootless blade directly abut said rotor shaft, said lateral protrusion of said first rooted blade contacting said first lateral protrusion of said rootless blade, said lateral protrusion of said second rooted blade contacting said second lateral protrusion of rootless blade, contact between said rootless blade and said first rooted blade and said second rooted blade radially secures said platform portion of said rootless blade in the abutting relationship with said rotor.
5. The rotor of claim 4, wherein said lateral protrusions on said first and said second rooted blades each have a smooth surface on the underside thereof, said lateral protrusions on said rootless blade each have a smooth surface on the radially outer side thereof, said smooth underside surfaces of said lateral protrusions of said first and said second rooted blades overlapping and contacting against said smooth radially outer surfaces on said lateral protrusions of said rootless blade, said relative motion between said rooted and rootless blades generating said friction force along said overlapped and contacted smooth surfaces on said platforms of rooted blades and said rootless blade to dampen said relative motion therebetween.
6. A rotor for an axial flow, elastic fluid turbine apparatus comprising: a shaft member having a plurality of axial grooves extending radially into said shaft and arranged circumferentially about the periphery thereof, said grooves defining a predetermined surface area of said shaft therebetween, a first and a Second blade having a root thereon, each root being disposed in adjacent axial grooves, each root having a predetermined circumferential dimension at the point on said root radially adjacent said surface of said shaft, said first and said second rooted blades each having a platform portion thereon spaced radially outward from said roots, said platforms each having a first and a second lateral protrusion thereon, the circumferential dimension on each blade between edges of said lateral protrusions being greater than said predetermined circumferential dimension of said root, said protrusions being spaced radially away from said shaft surface, each protrusion having a smooth underside surface thereon, said first protrusion on said first rooted blade and said second protrusion on said second rooted blade each circumferentially overlapping a portion of said surface area between said first and said second rooted blades, and, a rootless blade disposed between said first and said second rooted blades, said rootless blade having a platform portion having a first and a second lateral protrusion thereon, the greatest circumferential dimension of said rootless blade being disposed across said lateral protrusions, said platform portion of said rootless blade having a smooth underside surface thereon, said lateral protrusions of said rootless balde having smooth radially outer surfaces thereon, said underside surface of said rootless blade platform directly abutting against said surface of said shaft between first and said second rooted blades, said smooth, radially outer surface of said first protrusion of said rootless blade being radially beneath and overlapped by said smooth underside surface of said first lateral protrusion on said first rooted blade, said smooth radially outer surface of said second protrusion on said rootless blade being radially beneath and overlapped by said smooth, underside surface of said second lateral protrusion on said second rooted blade, the smooth underside surfaces of said lateral protrusions of said rooted blades overlapping, contacting and abrading against the radially outer surfaces of said lateral protrusions of said rootless blade to radially secure said rootless blade to said rotor, said rooted blades and said rootless blade being adapted so that relative motion between said rootless and said rooted blades generates a friction force between said smooth overlapping, contacting and abrading surfaces to dampen said relative motion between said rooted blades and said rootless blade.
7. The rotor of claim 6, wherein said root portion which radially secures said first and said second rooted blade to said shaft comprises a substantailly cylindrical knob portion; a substantially rectanguloid neck portion connected to said knob portion, and, a transition portion disposed radially between said knob portion and said neck portion, said knob portion being the radially innermost portion of said root when said root is disposed in one of said adjacent axial grooves, said predetermined dimension of said root being taken at a point on said neck portion adjacent said surface of said shaft, said transition portion between said knob and said neck being disposed so as to prevent stress concentration adjacent said root as said root radially secures said blade to said rotor.
8. The rotor of claim 7, wherein said rooted blades are attached to said shaft by said root portions thereof at a first point of fixity therebetween, and, said rootless blade is attached to said shaft by said rooted blades at a second point of fixity, said first point of fixity being radially inward on said shaft from said second point of fixity, said difference in points of fixity for said rooted blades on said rootless blade permitting relative motion to occur between said rooted blades and said rootless blade, said rotor further comprising means for axially securing said rootless blades to said shaft, sAid means comprising a pin member radially extending form said underside surface of said rootless blade, and a slot disposed circumferentially about said shaft surface, said direct abutment of said underside surface of said platform of said rootless blade against said surface of said shaft permitting said pin member to be radially inserted and radially engage said slot to axially secure said rootless blade to said shaft.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US357436A US3867069A (en) | 1973-05-04 | 1973-05-04 | Alternate root turbine blading |
| JP1416074A JPS5326243B2 (en) | 1973-05-04 | 1974-02-05 |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US357436A US3867069A (en) | 1973-05-04 | 1973-05-04 | Alternate root turbine blading |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| US3867069A true US3867069A (en) | 1975-02-18 |
Family
ID=23405588
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| US357436A Expired - Lifetime US3867069A (en) | 1973-05-04 | 1973-05-04 | Alternate root turbine blading |
Country Status (2)
| Country | Link |
|---|---|
| US (1) | US3867069A (en) |
| JP (1) | JPS5326243B2 (en) |
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4111603A (en) * | 1976-05-17 | 1978-09-05 | Westinghouse Electric Corp. | Ceramic rotor blade assembly for a gas turbine engine |
| US4904160A (en) * | 1989-04-03 | 1990-02-27 | Westinghouse Electric Corp. | Mounting of integral platform turbine blades with skewed side entry roots |
| US5183389A (en) * | 1992-01-30 | 1993-02-02 | General Electric Company | Anti-rock blade tang |
| EP0635623A1 (en) * | 1993-07-24 | 1995-01-25 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Rotor of a turbomachine |
| US20080304972A1 (en) * | 2007-06-07 | 2008-12-11 | Honeywell International, Inc. | Rotary body for turbo machinery with mistuned blades |
| WO2010112767A1 (en) * | 2009-04-02 | 2010-10-07 | Turbomeca | Turbine wheel with untuned blades comprising a damping device |
| WO2012009482A2 (en) * | 2010-07-13 | 2012-01-19 | Nature's Energy Banc | Connection mechanism for mounting blades for a wind turbine |
| US20130052020A1 (en) * | 2011-08-23 | 2013-02-28 | General Electric Company | Coupled blade platforms and methods of sealing |
| US20130343895A1 (en) * | 2012-06-25 | 2013-12-26 | General Electric Company | System having blade segment with curved mounting geometry |
| WO2014186028A1 (en) * | 2013-05-17 | 2014-11-20 | United Technologies Corporation | Tangential blade root neck conic |
| US10787916B2 (en) * | 2018-06-22 | 2020-09-29 | Rolls-Royce Corporation | Turbine wheel assembly with ceramic matrix composite components |
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|---|---|---|---|---|
| US2781998A (en) * | 1950-03-07 | 1957-02-19 | Centrax Power Units Ltd | Bladed rotors |
| US2843356A (en) * | 1954-04-05 | 1958-07-15 | Gen Electric | Turbo-machine rotor assembly |
| US2867408A (en) * | 1953-04-10 | 1959-01-06 | Parsons C A & Co Ltd | Axial locking of rotor blades for turbines and the like |
| US3002675A (en) * | 1957-11-07 | 1961-10-03 | Power Jets Res & Dev Ltd | Blade elements for turbo machines |
| US3702222A (en) * | 1971-01-13 | 1972-11-07 | Westinghouse Electric Corp | Rotor blade structure |
| US3761200A (en) * | 1970-12-05 | 1973-09-25 | Secr Defence | Bladed rotors |
-
1973
- 1973-05-04 US US357436A patent/US3867069A/en not_active Expired - Lifetime
-
1974
- 1974-02-05 JP JP1416074A patent/JPS5326243B2/ja not_active Expired
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2781998A (en) * | 1950-03-07 | 1957-02-19 | Centrax Power Units Ltd | Bladed rotors |
| US2867408A (en) * | 1953-04-10 | 1959-01-06 | Parsons C A & Co Ltd | Axial locking of rotor blades for turbines and the like |
| US2843356A (en) * | 1954-04-05 | 1958-07-15 | Gen Electric | Turbo-machine rotor assembly |
| US3002675A (en) * | 1957-11-07 | 1961-10-03 | Power Jets Res & Dev Ltd | Blade elements for turbo machines |
| US3761200A (en) * | 1970-12-05 | 1973-09-25 | Secr Defence | Bladed rotors |
| US3702222A (en) * | 1971-01-13 | 1972-11-07 | Westinghouse Electric Corp | Rotor blade structure |
Cited By (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4111603A (en) * | 1976-05-17 | 1978-09-05 | Westinghouse Electric Corp. | Ceramic rotor blade assembly for a gas turbine engine |
| US4904160A (en) * | 1989-04-03 | 1990-02-27 | Westinghouse Electric Corp. | Mounting of integral platform turbine blades with skewed side entry roots |
| US5183389A (en) * | 1992-01-30 | 1993-02-02 | General Electric Company | Anti-rock blade tang |
| FR2686941A1 (en) * | 1992-01-30 | 1993-08-06 | Gen Electric | ROTOR FIN WITH ANTI-OSCILLATING HEELS AND ROTOR OF A GAS TURBINE ENGINE COMPRISING SUCH FINS. |
| EP0635623A1 (en) * | 1993-07-24 | 1995-01-25 | Mtu Motoren- Und Turbinen-Union MàNchen Gmbh | Rotor of a turbomachine |
| US7887299B2 (en) * | 2007-06-07 | 2011-02-15 | Honeywell International Inc. | Rotary body for turbo machinery with mistuned blades |
| US20080304972A1 (en) * | 2007-06-07 | 2008-12-11 | Honeywell International, Inc. | Rotary body for turbo machinery with mistuned blades |
| WO2010112767A1 (en) * | 2009-04-02 | 2010-10-07 | Turbomeca | Turbine wheel with untuned blades comprising a damping device |
| FR2944050A1 (en) * | 2009-04-02 | 2010-10-08 | Turbomeca | DISCHARGED BLADE TURBINE WHEEL COMPRISING A DAMPING DEVICE |
| RU2525363C2 (en) * | 2009-04-02 | 2014-08-10 | Турбомека | Turbine wheel and turbomachine with such wheel |
| US8876472B2 (en) | 2009-04-02 | 2014-11-04 | Turbomeca | Turbine wheel having de-tuned blades and including a damper device |
| WO2012009482A2 (en) * | 2010-07-13 | 2012-01-19 | Nature's Energy Banc | Connection mechanism for mounting blades for a wind turbine |
| WO2012009482A3 (en) * | 2010-07-13 | 2014-03-27 | Nature's Energy Banc | Connection mechanism for mounting blades for a wind turbine |
| US20130052020A1 (en) * | 2011-08-23 | 2013-02-28 | General Electric Company | Coupled blade platforms and methods of sealing |
| US8888459B2 (en) * | 2011-08-23 | 2014-11-18 | General Electric Company | Coupled blade platforms and methods of sealing |
| EP2562355A3 (en) * | 2011-08-23 | 2018-04-11 | General Electric Company | Coupled blade platforms and methods of sealing |
| US20130343895A1 (en) * | 2012-06-25 | 2013-12-26 | General Electric Company | System having blade segment with curved mounting geometry |
| US10633985B2 (en) * | 2012-06-25 | 2020-04-28 | General Electric Company | System having blade segment with curved mounting geometry |
| WO2014186028A1 (en) * | 2013-05-17 | 2014-11-20 | United Technologies Corporation | Tangential blade root neck conic |
| US10982555B2 (en) | 2013-05-17 | 2021-04-20 | Raytheon Technologies Corporation | Tangential blade root neck conic |
| US10787916B2 (en) * | 2018-06-22 | 2020-09-29 | Rolls-Royce Corporation | Turbine wheel assembly with ceramic matrix composite components |
Also Published As
| Publication number | Publication date |
|---|---|
| JPS5326243B2 (en) | 1978-08-01 |
| JPS501205A (en) | 1975-01-08 |
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