CN104727860A - Locking spacer assembly - Google Patents
Locking spacer assembly Download PDFInfo
- Publication number
- CN104727860A CN104727860A CN201410858034.4A CN201410858034A CN104727860A CN 104727860 A CN104727860 A CN 104727860A CN 201410858034 A CN201410858034 A CN 201410858034A CN 104727860 A CN104727860 A CN 104727860A
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- China
- Prior art keywords
- extremity piece
- spacer block
- extremity
- internal surface
- platform
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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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
- F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
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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
- F01D5/32—Locking, e.g. by final locking blades or keys
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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
- F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
- F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
- F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A locking spacer assembly for securing adjacent rotor blades includes a first end piece configured to fit into a space between the platforms of adjacent rotor blades. The first end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. A second end piece is configured to fit into a space between the platforms. The second end piece comprises an outer surface and an inner surface. The outer surface has a profile that is adapted to project into the attachment slot. The inner surfaces of the first and second end pieces generally face each other. The first end piece and the second end piece are bonded together either directly or via a spacer block that is inserted between the inner surfaces.
Description
Technical field
The present invention relates generally to turbo machine.More specifically, the present invention relates to lockout interval assembly, it is for being affixed to the rotor disk of turbo machine by rotor blade.
Background technique
Various turbo machine (such as gas turbine or steamturbine), comprising: axle, be attached to multiple rotor disk of axle and be mounted to the various rotor blades of rotor disk.Conventional gas turbine comprises rotatable shaft, and wherein various rotor blade is mounted to the dish in its compressor and turbine.Each rotor blade comprises: thumbpiece, and forced air, combustion gas or other fluids (such as steam) flow above this thumbpiece; And platform, it, at the base portion place of thumbpiece, is defined for radial inner edge circle of air or fluid stream.
Rotor blade is removable typically, and therefore comprises suitable root and divide, and such as T-shaped root divides, and it is configured to the complementary attachment conduit in engagement rotator dish periphery.The root that this root can or enter for the root that axially enters or circumference, its with coil the corresponding shaft that formed in periphery to or circumferential conduit engage.Typical root comprises the neck and root projection with cross-sectional area, and this root is protruding extends into from root a pair side recesses being arranged in attachment conduit.
For circumferential root, single attachment conduit is formed between the continuous circumferential post of front and rear or hoop, and the rotate whole periphery of front and back of sub-disk of this post or garter spring circumferentially extends.The shape of cross section of circumference attachment conduit comprises by front and rear rotor disk post or binds round the side recesses limited, and during turbine operation, rotor disk post or hoop cooperate with the root projection of rotor blade, radially to keep independent blade.
In the compressor section of gas turbine, such as, rotor or compressor blade (particularly root member) to insert in circumferential conduit and around circumferential conduit, and rotate about 90 degree, to make the root of rotor blade projection contact with side recesses, carry out stop collar and to rotate the complete level of the rotor blade around sub-disk.Rotor blade comprises the platform at thumbpiece base portion place, and this platform can engage adjacently around conduit.In other embodiments, spacer element can be arranged in the circumferential conduit between adjacent rotor blades platform.As known in the art, once install all blades (and spacer element), the distance member designed especially has so typically been utilized to fill the final remaining space in attachment conduit an or more space.
For promoting that the final distance member common technology be inserted in circumferential conduit comprises the nonaxisymmetric loading conduit in rotor disk.Devise various regular intervals assembly and eliminate needs to the load conduit in rotor disk.But these assemblies comprise complicated device.The assembly of these routines is difficult to assembling usually, manufactures expensive, and can cause rotor unbalance.Therefore, there are the needs of the lockout interval assembly for improvement, this lockout interval assembly is relatively easily assembled in final space, and this final space is between the platform of the adjacent rotor blades (compressor of such as gas turbine and/or turbine rotor blade) of turbo machine.
Summary of the invention
Aspects and advantages of the present invention will describe below in the description which follows, or can become obvious from specification, or the acquistion by practice of the present invention.
One embodiment of the present of invention are a kind of lockout interval assemblies, its for insert adjacent rotor blades platform between circumference attachment conduit in.This lockout interval assembly comprises the first extremity piece, and this first extremity piece is configured to be coupled in the space between the platform of adjacent rotor blades.First extremity piece comprises outer surface and internal surface.Outer surface has the profile being suitable for charging in attachment conduit.Second extremity piece is configured to be coupled in the space between platform.Second extremity piece comprises outer surface and internal surface.Outer surface has the profile being suitable for charging in attachment conduit.Faced by the internal surface cardinal principle of the first and second extremity pieces each other.Spacer block is configured between the internal surface of insertion first and second extremity piece.Spacer block be bonded in the first extremity piece and the second extremity piece each.
Another embodiment of the present invention is a kind of lockout interval assembly, its for insert adjacent rotor blades platform between circumference attachment conduit in.This lockout interval assembly comprises the first extremity piece, and this first extremity piece is configured to be coupled in the space between the platform of adjacent rotor blades.First extremity piece comprises outer surface and internal surface.Outer surface has the profile being suitable for charging in attachment conduit.Second extremity piece is configured to be coupled in the space between platform.Second extremity piece comprises outer surface and internal surface.Outer surface has the profile being suitable for charging in attachment conduit.Faced by the internal surface cardinal principle of the first and second extremity pieces each other; First extremity piece is along the joint be limited between internal surface to be attached to described second extremity piece.
An alternative embodiment of the invention is a kind of turbo machine.This turbo machine comprises compressor, burner and turbine.At least one in compressor or turbine comprises rotor disk, and this rotor disk has front pillar and rear pillar.Front pillar and rear pillar limit the attachment conduit that circumference continuously extends at least in part.This turbo machine also comprises multiple rotor blade.Each in rotor blade extends from a platform of the correspondence multiple platform.Each in the plurality of platform is affixed to attachment conduit by the root extended internally.Lockout interval assembly is arranged in the space between at least two in multiple platform.Lockout interval assembly comprises the first extremity piece, and this first extremity piece is configured to be engaged in the space between the platform of adjacent rotor blades.First extremity piece comprises outer surface and internal surface.Outer surface has the profile being suitable for charging in attachment conduit.Second extremity piece is configured to be coupled in the space between platform.Second extremity piece comprises outer surface and internal surface.Outer surface has the profile being suitable for charging in attachment conduit.Faced by the internal surface cardinal principle of the first and second extremity pieces each other; First extremity piece is attached to the second extremity piece.
Technological scheme 1: a kind of lockout interval assembly, its for insert adjacent rotor blades platform between circumference attachment conduit in, comprising:
First extremity piece, it is configured to be coupled in the space between the platform of adjacent rotor blades, and described first extremity piece comprises outer surface and internal surface, and described outer surface has the profile being suitable for charging in attachment conduit;
Second extremity piece, it is configured to be coupled in the described space between described platform, and described second extremity piece comprises outer surface and internal surface, and described outer surface has and is suitable for charging into the profile in described attachment conduit, wherein, the described internal surface of described first and second extremity pieces is substantially in the face of each other; With
Spacer block, it is configured to insert between the described internal surface of described first and second extremity pieces, wherein, described spacer block be attached in described first extremity piece and described second extremity piece each.
Technological scheme 2: the lockout interval assembly according to technological scheme 1, it is characterized in that, also comprise jointing, described jointing is limited to described first extremity piece and described spacer block and between described second extremity piece and described spacer block, wherein, described spacer block combines along at least one in described jointing.
Technological scheme 3: the lockout interval assembly according to technological scheme 1, is characterized in that, described spacer block is combined by least one in welding or hard solder.
Technological scheme 4: the lockout interval assembly according to technological scheme 1, is characterized in that, described spacer block is combined by bonding coating.
Technological scheme 5: the lockout interval assembly according to technological scheme 1, is characterized in that, each in described first extremity piece, described second extremity piece and described spacer block limits the terrace part of described lockout interval assembly.
Technological scheme 6: the lockout interval assembly according to technological scheme 5, is characterized in that, each in described first extremity piece, described second extremity piece and described spacer block assigns to combine along described platform part.
Technological scheme 7: the lockout interval assembly according to technological scheme 1, is characterized in that, described spacer block engages with the bottom part of described attachment conduit.
Technological scheme 8: the lockout interval assembly according to technological scheme 1, it is characterized in that, also comprise the recess on the described internal surface being formed in described first and second extremity pieces, with the chimb be formed on described spacer block, wherein, described chimb is configured to be received in described recess when described spacer block inserts between described internal surface.
Technological scheme 9: a kind of lockout interval assembly, its for insert adjacent rotor blades platform between circumference attachment conduit in, comprising:
First extremity piece, it is configured to be coupled in the space between the platform of adjacent rotor blades, and described first extremity piece comprises outer surface and internal surface, and described outer surface has the profile being suitable for charging in attachment conduit;
Second extremity piece, it is configured to be coupled in the space between described platform, and described second extremity piece comprises outer surface and internal surface, and described outer surface has and is suitable for charging into the profile in described attachment conduit, wherein, the described internal surface of described first and second extremity pieces is contiguous each other; And
Wherein, described first extremity piece is along the joint be limited between described internal surface to be attached to described second extremity piece.
Technological scheme 10: the lockout interval assembly according to technological scheme 9, is characterized in that, described first extremity piece and described second extremity piece combine by welding.
Technological scheme 11: the lockout interval assembly according to technological scheme 9, is characterized in that, described first extremity piece and described second extremity piece are combined by hard solder.
Technological scheme 12: the lockout interval assembly according to technological scheme 9, is characterized in that, each in described first extremity piece and described second extremity piece limits the terrace part of described lockout interval assembly.
Technological scheme 13: the lockout interval assembly according to technological scheme 12, is characterized in that, described joint extends along described terrace part.
Technological scheme 14: the lockout interval assembly according to technological scheme 9, it is characterized in that, also comprise the recess on the described internal surface being formed in described first extremity piece, with the chimb be formed on the described internal surface of described second extremity piece, wherein, described chimb is configured to be received in described recess when described first and second extremity pieces are installed in described attachment conduit.
Technological scheme 15: a kind of turbo machine, comprising:
Compressor;
Burner; With
Turbine; And
Wherein, at least one in described compressor or described turbine comprises:
Rotor disk, it comprises front pillar and rear pillar, and described front pillar and rear pillar limit the attachment conduit that circumference continuously extends;
Multiple rotor blade, each in described multiple rotor blade extends from multiple platform, and wherein, each in described multiple platform is affixed to described attachment conduit by the root extended internally, and knows
Lockout interval assembly, it is arranged in the space between at least two in described multiple platform, and described lockout interval assembly comprises:
First extremity piece, it is configured to be coupled in the space between the platform of adjacent rotor blades, and described first extremity piece comprises outer surface and internal surface, and described outer surface has the profile being suitable for charging in attachment conduit;
Second extremity piece, it is configured to be coupled in the space between described platform, and described second extremity piece comprises outer surface and internal surface, and described outer surface has and is suitable for charging into the profile in described attachment conduit, wherein, the described internal surface of described first and second extremity pieces is substantially in the face of each other; And
Wherein, described first extremity piece is attached to described second extremity piece.
Technological scheme 16: the turbo machine according to technological scheme 15, is characterized in that, described first extremity piece is along the joint be limited between described internal surface to be attached to described second extremity piece.
Technological scheme 17: the turbo machine according to technological scheme 15, is characterized in that, described first extremity piece is attached to described second extremity piece by least one in welding or hard solder.
Technological scheme 18: the turbo machine according to technological scheme 15, it is characterized in that, described first extremity piece and described second extremity piece limit the terrace part of described lockout interval assembly, and wherein, described first extremity piece and described second extremity piece combine along described terrace part.
Technological scheme 19: the turbo machine according to technological scheme 15, it is characterized in that, also comprise spacer block, described spacer block is configured to insert between the described internal surface of described first and second extremity pieces, wherein, described first extremity piece is attached to described second extremity piece by described spacer block.
Technological scheme 20: the turbo machine according to technological scheme 19, it is characterized in that, described first extremity piece, described second extremity piece and described spacer block limit the terrace part of described lockout interval assembly, wherein, each in described first extremity piece, described second extremity piece and described spacer block combines along described terrace part.
After reading this specification, those skilled in the art will understand the characteristic sum aspect of this kind and other embodiments better.
Accompanying drawing explanation
Complete and disclosing of can realizing of the present invention, comprises its preferred forms to those skilled in the art, more specifically states comprising in the remainder of this specification quoted of accompanying drawing, in the accompanying drawings:
Fig. 1 is the functional diagram of demonstration gas turbine within the scope of the invention;
Fig. 2 is the part sectioned view entering the root of rotor blade and the embodiment of attachment conduit structure for circumference;
Fig. 3 is the fragmentary, perspective view of demonstration rotor disk, and this demonstration rotor disk comprises the insertable final or loading space of lockout interval assembly;
Fig. 4 is according to an embodiment of the invention, the top view of the part of rotor disk as shown in Figure 3;
Fig. 5 is the exploded view of the component of the embodiment of lockout interval assembly according to various aspect of the present invention;
Fig. 6, Fig. 7, Fig. 8 and Fig. 9 are the continuous ssembly drawings of lockout interval assembly according to an embodiment of the invention;
Figure 10 provides a part of sectional view of rotor disk, and this rotor disk comprises lockout interval assembly according to an embodiment of the invention;
Figure 11 is the top view of a part for rotor disk, and this rotor disk comprises lockout interval assembly as shown in Figure 10.
Build list table
10 gas turbines
12 compressor sections
14 compressors
16 burning blocks
18 burners
20 turbines
22 turbines
24 axles
26 longitudinal center lines
28 rotor wheel or dish
30 rotor blades
32 compressor rotor blades
34 turbine rotor blades
36 longitudinal centerline axis
38 airfoil parts
40 leading edges
42 trailing edges
44 working fluids
46 compression working fluids
48 combustion gas
50 platforms
52 roots divide
54 attachment conduits
& rear pillar or hoop component before 56
58 is protruding
60 side recesses
62 recessed wall sections
64 wall portion
66 spacer elements
68 final/to be loaded into space
70 circumferential width
71-99 does not use
100 lockout interval assemblies
102 first extremity pieces
104 second extremity pieces
106 spacer blocks
108 circumferential width
110 terrace parts
112 roots divide
114 radial heights
116 axial lengths
118 circumferential width
120 first internal surfaces
122 outer surfaces
124 side surfaces
126 first side recesses
128 first projections
130 arc grooves
132 recesses
134 chimbs
136 terrace parts
138 roots divide
140 radial heights
142 axial lengths
144 circumferential width
146 second internal surfaces
148 outer surfaces
150 side surfaces
152 second side recesses
154 second projections
156 arc grooves
158 recesses
160 chimbs
162 circumferential width
164 terrace parts
166 bottom wall portions
168 interfaces/jointing
170 interfaces/jointing.
Embodiment
Now make detailed reference to existing embodiment of the present invention, one or more example of the present invention is shown in the drawings.Detailed description use numeral and alphabetic flag refer to the feature in accompanying drawing.Identical or similar mark in drawing and description has been used in reference to identical or similar portions of the present invention.As used in this article, term " first ", " second " and " the 3rd " can use interchangeably, a component and another to be distinguished, and are not intended to the position or the significance that represent independent component.
As used in this article, term " upstream " and " downstream " mean the opposite direction relative to fluid stream in fluid path.Such as, " upstream " means the direction that fluid flows from it, and " downstream " means the direction of direction of flow.Term " radially " means as the opposite direction in lower plane, and this plane is basically perpendicular to the longitudinal center line of concrete component, and term " axially " means as the opposite direction in lower plane, and this plane is basically parallel to the longitudinal center line of concrete component.
So that the present invention to be described, instead of to limit form of the present invention each example is provided.In fact, it will be apparent to one skilled in the art that and can modify in the present invention and modification and do not depart from its scope or spirit.Such as, the feature of the part illustrating or be described as an embodiment can be used in another embodiment, to form another embodiment.Therefore, be intended to, the present invention covers and falls into claims and this kind of amendment in the scope of their equivalent and modification.
Although for illustrative purposes, by under the background of gas turbine, example embodiment of the present invention is briefly described, but the person skilled in the art will easily understand, embodiments of the invention can be applicable to any turbo machine of the rotation blade having axle and be attached to axle, such as steamturbine etc., and be not limited to gas turbine, unless clearly describe in the claims.
Referring now to accompanying drawing, wherein throughout accompanying drawing, the element that identical numeral is identical, Fig. 1 provides the functional diagram of an embodiment of turbo machine, and in this case, turbo machine is the demonstration gas turbine 10 that can comprise various embodiment of the present invention.Should be understood that, the disclosure is not limited to gas turbine, and on the contrary, steamturbine or any other suitable turbo machine are all in the scope of the present disclosure and spirit.As shown, gas turbine 10 generally includes: compressor section 12, and it comprises the compressor 14 being arranged in gas turbine 10 upstream extremity; Burning block 16, it has at least one burner 18 in compressor 14 downstream; With turbine 20, it comprises the turbine 22 in burning block 14 downstream.Axle 24 extends through compressor 14 and/or turbine 22 at least in part along the longitudinal center line 26 of gas turbine 10.In concrete structure, axle 24 can be made up of multiple independent axle.
Multiple rotor wheel or dish 28 are arranged coaxially along axle 24 in compressor 14 and/or turbine 22.Each rotor disk 28 is configured to the rotor blade 30 holding multiple radial direction extension, rotor blade 30 surrounding rotor dish 28 circumferentially interval, and is fixed to rotor disk 28 removedly.Rotor blade 30 can be configured to use in compressor 14, such as compressor rotor blade 32, or for using in turbine 22, such as turbine rotor blade or turbine rotor blade 34.Each blade 30 has longitudinal center's axis 36, and comprises thumbpiece part 38, and thumbpiece part 38 has leading edge 40 and trailing edge 42.
In operation, be sent in compressor 14 by working fluid 44 (such as air), at this, when working fluid 44 sends towards burning block 16, working fluid 44 is by compressor rotor blade 32 partly progressive compression.Compression working fluid 46 flows out from compressor 14, and is supplied to burning block 16.Compression working fluid 46 is dispensed to each in burner 18, this itself and fuel mix to provide ignition mixture.This ignition mixture burning with produces relatively-high temperature and high speed under combustion gas 48.Combustion gas 48 are sent through turbine 22, at this, heat and kinetic energy are passed to turbine rotor blade 34, thus cause axle 24 to rotate.In a particular application, axle 24 is attached to generator (not shown) to produce electric power.
Fig. 2 is the amplification profile of the part of the demonstration rotor disk 28 comprising demonstration the rotor blade 30 and attachment conduit structure with T-shaped root.As shown in Figure 2, each rotor blade 30 also can comprise platform 50, and in the operation period of gas turbine 10, this platform 50 is provided for radial inner edge circle of air stream, combustion gas stream or other fluid streams (such as steam) above thumbpiece 38.In addition, the root that each rotor blade 30 comprises one divides 52, and it extends radially inwardly from platform 50.As known in the field, in root divide 52 to slip into attachment conduit 54 that circumference extends and along attachment conduit 54, this attachment conduit 54 is limited at least in part by the front and rear hoop of rotor disk 28 or post component 56.In alternative, the attachment conduit 54 that circumference extends can machining, casting or otherwise limited by rotor disk 28.
Root divides 52 can comprise projection 58, and projection 58 is received in the side recesses 60 be limited in attachment conduit 54, and is limited at least in part by the recessed wall section 62 of post component 56.Front and rear post component 56 and/or rotor disk 28 can limit the wall portion 64 of attachment conduit 54 further.Should easily understand, the root provided in fig. 2 divide 52 and attachment conduit 54 structure only for illustrating object, and root and conduit structure can change widely in the scope and spirit of this theme.
Fig. 3 is the fragmentary, perspective view of the part of demonstration rotor disk 28, and example configurations is being attached the multiple rotor blades 30 in conduit 54 (Fig. 2) particularly, and this attachment conduit 54 is between the front and rear post component 56 of rotor disk 28.As shown in Figures 2 and 3, each in rotor blade 30 comprises platform 50.As in known in the art, as shown in Figure 3, regular intervals part 66 is arranged between the platform 50 of adjacent rotor blades 30.
Fig. 4 is according to an embodiment of the invention, the top view of the part of rotor disk 28 as shown in Figure 3.As shown in Figure 3, there is one or more of circumferential width 70 final or be loaded into space 68 and be limited between adjacent rotor blades 30 platform 50.Final or loading space 68 is often used in the assembling of rotor blade 30 pairs of rotor disks 28 and/or is inserted by rotor blade 30 during dismantling in attachment conduit 54.In a particular embodiment, as shown in Figure 4, final or be loaded into space 68 by below in greater detail the various embodiments of lockout interval assembly 100 fill.
Should be understood that, in the particular embodiment, lockout interval assembly 100 can be used for the final space 68 of filling between the platform 50 of adjacent rotor blades 30, and this rotor blade 30 comprises the compressor rotor blade 32 being positioned at compressor 14 and/or the turbine rotor blade 34 being positioned at turbine 22.Therefore, lockout interval assembly 100 will be described below between the platform 50 for being arranged on adjacent rotor blades 30 usually, and wherein, platform 50 can be the part of compressor rotor blade 32 or turbine rotor blade 34, to comprise two methods completely.
Fig. 5 is according to an embodiment of the invention, is referred to herein as the exploded view of the component of the lockout interval assembly 100 of " assembly 100 ".As shown in Figure 5, assembly 100 comprises the first extremity piece 102, second extremity piece 104 and spacer block 106.First and second extremity pieces 102,104 are configured to be coupled in the final space 66 between the platform 50 of adjacent rotor blades 30.Therefore, extremity piece 102,104 has following arbitrary dimension structure, and it makes width, length, thickness or any other feature that extremity piece 102,104 can be inserted between platform 50.Such as, extremity piece 102,104 can have circumferential width 108 (Fig. 4) usually, so as to paste and be engaged in adjacent rotor blades 30 platform 50 between.
As shown in Figure 5, the first extremity piece 102 comprises terrace part 110 and root divides 112.Terrace part 110 has radial height 114 usually, axial length 116 and circumferential width 118.Root divides 112 to extend radially inwardly from terrace part 110.Terrace part 110 and root divide 112 restriction first internal surface 120 and outer surfaces 122.In one embodiment, the first internal surface 120 is approximately perpendicular to the axial plane and/or longitudinal center line that extend through lockout interval assembly 100 and/or the first extremity piece 102.In an alternative embodiment, the first internal surface 120 can be angled about plane radially, and this plane orthogonal is radially in axial plane and/or longitudinal center line.In one embodiment, the first internal surface 120 is configured to mate with the side surface 124 of spacer block 106.Such as, the shape of the first internal surface 120 and side surface 124 and/or angle can be consistent.
Outer surface 122 has the profile dividing 112 restrictions along root.This profile is suitable for charging in the first side recesses 126 of attachment conduit 54.Such as, this profile can comprise the first projection 128.First projection 128 can be shaped to charges in the first side recesses 126.Outer surface 122 is flexible or otherwise formalize, so as with the Similar Broken Line of post component 56.Should easily know, the first projection 128 can have the profile of any expectation, and without the need for contoured illustrated in Fig. 5.Major part is depended on given shape and the structure of attachment conduit 54 by the profile of the first projection 128.
In a particular embodiment, arc groove 130 or other stress relief feature is limited close with upper/lower positions by the first extremity piece 102, such as transition or chamfering, in this position, the first projection 128 divides 112 roughly axially outwards limit or extend from the root of the first extremity piece 102.Arc groove 130 can be comprised to provide low stress point or the position for stress elimination on the first extremity piece 102.As will later be shown, arc groove 130 can be positioned at root around the corner and divide on 112, and this turning is formed in front pillar or between rear pillar component 56 and the first side recesses 126.
As shown in Figure 5, recess 132 is formed on the terrace part 110 of the first extremity piece 102.Recess 132 can be positioned near the first internal surface 120 substantially.Recess 132 can be configured to or be shaped to and receive complementary chimb or protruding 134, on the side surface 124 that this complementary chimb or protruding 134 is formed in spacer block 106 and/or near.Such as, recess 132 and chimb 134 can be rectangle, trapezoidal, arc or any shape, use to produce interlocked between the first extremity piece 102 and spacer block 106.
As shown in Figure 5, the second extremity piece 104 comprises terrace part 136 and root divides 138.Terrace part 136 generally has radial height 140, axial length 142 and circumferential width 144.Root divides 138 to extend radially inwardly from terrace part 136.Terrace part 136 and root divide 138 restriction second internal surface 146 and outer surfaces 148.In one embodiment, the second internal surface 146 is approximately perpendicular to the axial plane and/or longitudinal center line that extend through lockout interval assembly 100 and/or the second extremity piece 104.In an alternative embodiment, the second internal surface 146 is angled about plane radially, and this plane orthogonal is radially in axial plane and/or longitudinal center line.In one embodiment, the second internal surface 146 is configured to mate with the side surface 150 of spacer block 106.Such as, the shape of the second internal surface 146 and side surface 150 and/or angle consistent.
Outer surface 148 has the profile dividing 138 restrictions along root.The profile of outer surface 148 is suitable for charging in the second side recesses 152 of attachment conduit 54.Such as, this profile can comprise the second projection 154.Second projection 154 can be shaped to charges in the second side recesses 152.Outer surface 148 flexible or be otherwise shaped to so as with the Similar Broken Line of post component 56.Should easily know, the second projection 154 can have the profile of any expectation, and does not need to have illustrative contoured in Fig. 5.Major part is depended on given shape and the structure of attachment conduit 54 by the profile of the second projection 154.
In a particular embodiment, by the second extremity piece 104 such as, close to limiting arc groove 156 or other stress relief feature with upper/lower positions, transition or chamfering, in this position, the second projection 140 divides 138 roughly axially outwards limit or extend from the root of the second extremity piece 104.Arc groove 156 can be comprised to provide low pressure force or the position for stress elimination on the second extremity piece 104.As will later be shown, arc groove 156 can be positioned at root around the corner and divide on 138, and this turning is formed in front pillar or between rear pillar component 56 and the second side recesses 152.
As shown in Figure 5, recess 158 can be formed on the terrace part 136 of the second extremity piece 104.Recess 158 can be positioned to substantially be close to the second internal surface 146.Recess 158 can be configured to or be shaped to and receive complementary chimb or protruding 160, on the side surface 150 that this complementary chimb or protruding 160 is formed in spacer block 106 and/or near.Such as, recess 158 and chimb 160 can be rectangle, trapezoidal and arc or any shape, use to produce interlocked between the second extremity piece 104 and spacer block 106.
In a particular embodiment, as shown in Figure 4, spacer block 106 is also configured to be engaged between the platform 50 of adjacent rotor blades 30.Such as, as shown in Figure 5, spacer block 106 can have circumferential width 162 substantially, to be snugly engaged between platform 50 (Fig. 4).Although substantially show for being rectangle, but spacer block 106 can be sawtooth, Z-shaped, arc maybe can have following arbitrary dimension structure, and it makes width, length, thickness or any other feature make spacer block 106 can insert between the first and second internal surfaces 120,146 of the first and second extremity pieces 102,104.In illustrative embodiment, as Fig. 4 probably illustrates, when extremity piece 102,104 and spacer block 106 insert in attachment conduit 54, the first internal surface 120 substantially faces sidewall 124 and the second internal surface 146 faces sidewall 150.Spacer block 106 comprises terrace part 164 substantially.
Fig. 6, Fig. 7, Fig. 8 and Fig. 9 are the continuous ssembly drawings of lockout interval assembly 100 according to an embodiment of the invention.As shown in Figure 6, the root of the second extremity piece 104 divides in the 138 attachment conduits 54 of falling between opposing sidewall portions 64.As shown in Figure 7, the second projection 154 is located so that it extends in the second side recesses 152.As shown in Figure 7, the root of the first extremity piece 102 divides 112 to fall in attachment conduit 54, contiguous second extremity piece 104, makes the first internal surface 120 and the second internal surface 146 in the face of each other.As shown in Figure 8, then the first projection 128 is located so that it extends in the first side recesses 126.The assembling sequence of the first extremity piece 102 and the second extremity piece 104 can be put upside down.
As also illustrated in Fig. 8 and 9, then spacer block 106 inserts between the first and second internal surfaces 120,146.Spacer block 106 temporarily can be held in place by being press-fitted between the first and second internal surfaces of the first and second extremity pieces 102,104 is incompatible, and/or is held in place by chimb 134,160.In addition or alternatively, as shown in Figure 9, spacer block 106 can extend radially inwardly, to engage with the bottom wall portion 166 of attachment conduit 54.Then spacer block 106 can be attached in position along at least one interface or jointing 168, this at least one interface or jointing 168 are along the first and second internal surface 120,146 and side surfaces 124, a restriction in the intersection point of 150, thus by this lockout interval assembly 100 lock in place, and adjacent rotor blades 30 is affixed to rotor disk 28.In a particular embodiment, spacer block 106 is by welding, hard solder, bonding coating or well known in the art for combining in conjunction with any suitable associated methods of metal construction by the operating environment that is applicable to rotor blade 30.
Figure 10 provides the sectional view of a part for rotor disk 28, and this rotor disk 28 comprises the alternative of lockout interval assembly 100 according to an embodiment of the invention.Figure 11 is the top view of a part for rotor disk 28, and this rotor disk 28 comprises the lockout interval assembly 100 shown in Figure 10.In an alternative embodiment, as shown in Figure 10, lockout interval assembly 100 comprises the first extremity piece 102 and the second extremity piece 104 constructed herein previously describedly.As directed, when being installed in attachment conduit 54, the internal surface 120 of the first extremity piece 102 and the internal surface 146 of the second extremity piece 104 adjoin.Interface or jointing 170 are limited between the internal surface 120 of the first extremity piece 102 and the internal surface 146 of the second extremity piece 104.First extremity piece 102 and the second extremity piece 104 combine along jointing 170.In a particular embodiment, the first extremity piece 102 and the second extremity piece 104 combine for any suitable associated methods in conjunction with metal construction by least one in welding, hard solder, bonding coating or by the well known in the art of operating environment being applicable to rotor blade 30.In this embodiment, recess 172 can be formed in any one in the first or second extremity piece 102,104, and projection or chimb 174 can be formed on another in the first or second extremity piece 102,104, are therefore held in place by assembly during installation.The terrace part 136 of the terrace part 110 of the first extremity piece 102 and the second extremity piece 104 limits the terrace part of locking distance member 100, and jointing extends along the terrace part of lockout interval assembly.
In this configuration, one in the first or second extremity piece 102,104 is inserted in attachment conduit 54, and another of the first or second extremity piece 102,104 tilts to enter in attachment conduit 54, makes the first and second internal surfaces 120,146 contiguous.Then first and second extremity pieces 102,104 combine along jointing 170, thus by lockout interval assembly 100 locks in place, and adjacent rotor blades 30 is affixed to rotor disk 28.
The open the present invention of this written explanation use-case, comprises preferred forms, and enables any those skilled in the art put into practice the present invention, comprise and manufacture and use any device or system, and perform the method for any merging.Patentable scope of the present invention is defined by the claims, and can comprise other examples that those skilled in the art expect.If other examples of this kind comprise not different from the literal language of claim structural elements, if or other examples of this kind comprise and the equivalent structural elements of the literal language of claim without marked difference, then other examples of this kind intention within the scope of the claims.
Claims (10)
1. a lockout interval assembly, its for insert adjacent rotor blades platform between circumference attachment conduit in, comprising:
First extremity piece, it is configured to be coupled in the space between the platform of adjacent rotor blades, and described first extremity piece comprises outer surface and internal surface, and described outer surface has the profile being suitable for charging in attachment conduit;
Second extremity piece, it is configured to be coupled in the described space between described platform, and described second extremity piece comprises outer surface and internal surface, and described outer surface has and is suitable for charging into the profile in described attachment conduit, wherein, the described internal surface of described first and second extremity pieces is substantially in the face of each other; With
Spacer block, it is configured to insert between the described internal surface of described first and second extremity pieces, wherein, described spacer block be attached in described first extremity piece and described second extremity piece each.
2. lockout interval assembly according to claim 1, it is characterized in that, also comprise jointing, described jointing is limited to described first extremity piece and described spacer block and between described second extremity piece and described spacer block, wherein, described spacer block combines along at least one in described jointing.
3. lockout interval assembly according to claim 1, is characterized in that, described spacer block is combined by least one in welding or hard solder.
4. lockout interval assembly according to claim 1, is characterized in that, described spacer block is combined by bonding coating.
5. lockout interval assembly according to claim 1, is characterized in that, each in described first extremity piece, described second extremity piece and described spacer block limits the terrace part of described lockout interval assembly.
6. lockout interval assembly according to claim 5, is characterized in that, each in described first extremity piece, described second extremity piece and described spacer block assigns to combine along described platform part.
7. lockout interval assembly according to claim 1, is characterized in that, described spacer block engages with the bottom part of described attachment conduit.
8. lockout interval assembly according to claim 1, it is characterized in that, also comprise the recess on the described internal surface being formed in described first and second extremity pieces, with the chimb be formed on described spacer block, wherein, described chimb is configured to be received in described recess when described spacer block inserts between described internal surface.
9. a lockout interval assembly, its for insert adjacent rotor blades platform between circumference attachment conduit in, comprising:
First extremity piece, it is configured to be coupled in the space between the platform of adjacent rotor blades, and described first extremity piece comprises outer surface and internal surface, and described outer surface has the profile being suitable for charging in attachment conduit;
Second extremity piece, it is configured to be coupled in the space between described platform, and described second extremity piece comprises outer surface and internal surface, and described outer surface has and is suitable for charging into the profile in described attachment conduit, wherein, the described internal surface of described first and second extremity pieces is contiguous each other; And
Wherein, described first extremity piece is along the joint be limited between described internal surface to be attached to described second extremity piece.
10. lockout interval assembly according to claim 9, is characterized in that, described first extremity piece and described second extremity piece combine by welding.
Applications Claiming Priority (2)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14/055114 | 2013-10-16 | ||
| US14/055,114 US20150101350A1 (en) | 2013-10-16 | 2013-10-16 | Locking spacer assembly |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104727860A true CN104727860A (en) | 2015-06-24 |
Family
ID=52738165
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410858034.4A Pending CN104727860A (en) | 2013-10-16 | 2014-10-16 | Locking spacer assembly |
Country Status (5)
| Country | Link |
|---|---|
| US (1) | US20150101350A1 (en) |
| JP (1) | JP2015078688A (en) |
| CN (1) | CN104727860A (en) |
| CH (1) | CH708764A2 (en) |
| DE (1) | DE102014114555A1 (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113251000A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Locking method of aircraft engine blade |
Families Citing this family (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US9512732B2 (en) | 2013-10-16 | 2016-12-06 | General Electric Company | Locking spacer assembly inserted between rotor blades |
| US9416670B2 (en) | 2013-10-16 | 2016-08-16 | General Electric Company | Locking spacer assembly |
| US9341071B2 (en) | 2013-10-16 | 2016-05-17 | General Electric Company | Locking spacer assembly |
| US9518471B2 (en) | 2013-10-16 | 2016-12-13 | General Electric Company | Locking spacer assembly |
| US9464531B2 (en) | 2013-10-16 | 2016-10-11 | General Electric Company | Locking spacer assembly |
| KR101884712B1 (en) * | 2016-12-21 | 2018-08-03 | 두산중공업 주식회사 | Locking spacer for rotor blade |
| US10465699B2 (en) * | 2017-01-26 | 2019-11-05 | DOOSAN Heavy Industries Construction Co., LTD | Compressor blade locking mechanism in disk with tangential groove |
| EP3752716B1 (en) | 2018-03-28 | 2021-10-13 | Siemens Energy Global GmbH & Co. KG | Locking spacer assembly, corresponding blade assembly and method for installing a locking spacer |
| FR3081501B1 (en) * | 2018-05-23 | 2020-09-18 | Safran Aircraft Engines | SHUTTER FOR TURBOREACTOR WITH ABSENT RECTIFIER VANE |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE10346239A1 (en) * | 2003-10-06 | 2005-04-21 | Alstom Technology Ltd Baden | Method for fixing the blading of a turbomachine and fixing device |
-
2013
- 2013-10-16 US US14/055,114 patent/US20150101350A1/en not_active Abandoned
-
2014
- 2014-10-07 DE DE201410114555 patent/DE102014114555A1/en not_active Withdrawn
- 2014-10-08 JP JP2014206864A patent/JP2015078688A/en active Pending
- 2014-10-15 CH CH01569/14A patent/CH708764A2/en not_active Application Discontinuation
- 2014-10-16 CN CN201410858034.4A patent/CN104727860A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113251000A (en) * | 2020-02-13 | 2021-08-13 | 中国航发商用航空发动机有限责任公司 | Locking method of aircraft engine blade |
Also Published As
| Publication number | Publication date |
|---|---|
| JP2015078688A (en) | 2015-04-23 |
| US20150101350A1 (en) | 2015-04-16 |
| DE102014114555A1 (en) | 2015-04-16 |
| CH708764A2 (en) | 2015-04-30 |
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