CN206647139U - Turbine nozzle vane listrium seal structure - Google Patents
Turbine nozzle vane listrium seal structure Download PDFInfo
- Publication number
- CN206647139U CN206647139U CN201720356918.9U CN201720356918U CN206647139U CN 206647139 U CN206647139 U CN 206647139U CN 201720356918 U CN201720356918 U CN 201720356918U CN 206647139 U CN206647139 U CN 206647139U
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- groove
- listrium
- obturage
- obturages
- blade
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Abstract
It the utility model is related to turbo blade seal structure design field, a kind of turbine nozzle vane listrium seal structure is specifically provided, including the first blade listrium, the second blade listrium and obturage piece, first blade listrium is provided with first and obturages groove, second blade listrium is provided with second and obturages groove, first, which obturages the size and dimension of groove and second, obturages that groove is identical, first obturage position of the groove on the first blade listrium with second obturage groove the second blade listrium it is upper put it is corresponding；First, which obturages groove and second, obturages the one end of groove on the nozzle ring axial direction and is outwardly open, other end closing, and first, which obturages groove and second, obturages groove composition listrium and obturage groove；Obturage piece and be arranged on first and obturage groove and second and obturage in groove, obturage piece to obturage one end that the blind end of groove is in contact with the listrium be in bending-like, this is bending section in the dogleg section of bending-like one end, and the both ends of bending section are born against on the upper groove surface and lower groove face for obturaging groove in the listrium.
Description
Technical field
It the utility model is related to turbo blade seal structure design field, more particularly to a kind of turbine nozzle vane
Listrium seal structure.
Background technology
Nozzle ring is made up of some groups of turborotors, is deposited between turborotor adjacent blades listrium
In circular gap, it is necessary to which seal structure is obturaged, the leakage of combustion gas is reduced.To reduce air loss, in listrium lateral layout
Obturage groove and piece assembling will be obturaged wherein, reach the purpose for reducing gas leakage, improving turbine efficiency.
The groove of obturaging of a portion is designed as one end closing, the structure type of another end opening so that obturage in groove
Obturage piece and be in free state, when being overturn in assembling or transportation, being inverted blade, sector-meeting hair is obturaged without any stop
Raw slide even comes off, and causes listrium gap to obturage failure, leaks combustion gas.
Utility model content
The defects of to overcome above-mentioned prior art to exist, the utility model provide a kind of turbine nozzle vane listrium envelope
Tight structure, including the first blade listrium, the second blade listrium and obturage piece, the first blade listrium it is relative with the second blade listrium
Side be provided with first and obturage groove, the side relative with the first blade listrium of the second blade listrium is provided with second and obturages groove,
One, which obturages the size and dimension of groove and second, obturages that groove is identical, and first obturages position and second of the groove on the first blade listrium
Obturage groove the second blade listrium it is upper put it is corresponding；
First, which obturages groove and second, obturages the wherein one end of groove on the nozzle ring axial direction and is outwardly open, another
End seal is closed, and one end of closing is referred to as blind end, and first, which obturages groove and second, obturages groove composition listrium and obturage groove；
Obturage both sides of the piece on the nozzle ring axial direction and be separately positioned on first and obturage groove and second and obturage in groove,
Obturage piece to obturage one end that the blind end of groove is in contact with the listrium be in bending-like, should be in the dogleg section of bending-like one end
For bending section, the both ends of bending section are born against on the upper groove surface and lower groove face for obturaging groove in the listrium.
Preferably, first groove is obturaged and second to obturage groove be straight trough.
Preferably, obturage length of the piece on the nozzle ring axial direction and obturage groove equal to first and be oriented in the turbine
Length on device axial direction.
The utility model provides a kind of turbine nozzle vane listrium seal structure, is made by flexible bending section
Obturaging piece has an auto-lock function, and bending section, which will obturage piece and be fixed on, to be obturaged in groove, prevent turbo blade upset, be inverted or other
In the case of cause to obturage piece and come off.
Brief description of the drawings
Fig. 1 is the schematic side view of turbine nozzle vane listrium seal structure；
Fig. 2 is the schematic elevation view of turbine nozzle vane listrium seal structure；
Fig. 3 is the axonometric drawing of turbine nozzle vane listrium seal structure.
Reference：First blade listrium 1, the second blade listrium 2, piece 3 is obturaged, first obturages groove 4, and second obturages groove 5,
Bending section 6, listrium gap 7.
Embodiment
To make the purpose, technical scheme and advantage that the utility model is implemented clearer, below in conjunction with the utility model
Accompanying drawing in embodiment, the technical scheme in the embodiment of the utility model is further described in more detail.In the accompanying drawings, from beginning
Same or similar element is represented to same or similar label eventually or there is the element of same or like function.Described reality
It is the utility model part of the embodiment to apply example, rather than whole embodiments.Below with reference to the embodiment of accompanying drawing description
It is exemplary, it is intended to for explaining the utility model, and it is not intended that to limitation of the present utility model.It is new based on this practicality
Embodiment in type, the every other implementation that those of ordinary skill in the art are obtained under the premise of creative work is not made
Example, belong to the scope of the utility model protection.
In description of the present utility model, it is to be understood that term " " center ", " longitudinal direction ", " transverse direction ", "front", "rear",
The orientation or position relationship of the instruction such as "left", "right", " vertical ", " level ", " top ", " bottom ", " interior ", " outer " is based on accompanying drawing institutes
The orientation or position relationship shown, it is for only for ease of description the utility model and simplifies description, rather than indicates or imply and be signified
Device or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this practicality
The limitation of novel protected scope.
The utility model is described in further detail below by specific embodiment.
Specific embodiment：
As depicted in figs. 1 and 2, the utility model provides a kind of turbine nozzle vane listrium seal structure, including
One blade listrium 1, the second blade listrium 2 and piece 3 is obturaged, the side relative with the second blade listrium 2 of the first blade listrium 1 is opened
There is first to obturage groove 4, the side relative with the first blade listrium 1 of the second blade listrium 2 is provided with second and obturages groove 5, the first envelope
It is identical that the size and dimension of tight groove 4 with second obturages groove 5, and in the present embodiment, first obturages groove 4 and second to obturage groove 5 be straight
Groove, i.e., both are linear pattern groove；
As shown in Fig. 2 leaving listrium gap 7 between the first blade listrium 1 and the second blade listrium 2, first, which obturages groove 4, exists
Position on first blade listrium 1 obturages that the position on the second blade listrium 2 of groove 5 is corresponding, i.e., first obturages groove 4 with second
Notch position and second obturages the notch position of groove 5 relative to the axial symmetry of listrium gap 7；
First, which obturages groove 4 and second, obturages the wherein one end of groove 5 on the nozzle ring axial direction and is outwardly open, and claims
For openend, other end closing, one end of closing is referred to as blind end, and openend represents that the section communicates with the external world, and blind end is
Represent that the end does not communicate with the external world, belong to blind slot structure, the end face of blind end is referred to as axial groove bottom, and first obturages groove 4 and second
Obturage the composition listrium of groove 5 and obturage groove；
As shown in Figures 2 and 3, both sides of the piece 3 on the nozzle ring axial direction are obturaged it is separately positioned on first and obturages
Groove 4 and second is obturaged in groove 5, obturage piece 3 to obturage one end that the blind end of groove is in contact with the listrium be in bending-like, this is in
The dogleg section of bending-like one end is bending section 6, the both ends of bending section 6 bear against the listrium obturage groove upper groove surface and
On lower groove face, while bending section 6 is also in contact with the axial groove bottom, when piece 3 is obturaged in installation, will obturage the bending section 6 of piece 3
The listrium is pushed into first from the openend to obturage in groove, push-in is then proceeded to and obturages piece 3, until bending section 6 touches institute
State axial groove bottom, in the present embodiment, obturage length of the piece 3 on nozzle ring axial direction and obturage groove 4 in the whirlpool equal to first
The length on guider axial direction is taken turns, therefore the other end for obturaging piece 3 is concordant with the opening；
Because bending section 6 has certain elasticity, bending section 6 is resisted against the listrium in the presence of elastic force and obturages groove
On upper groove surface and lower groove face, self-locking is formed, when guide vane is under inversion, rollover states, can prevent that obturaging piece 3 comes off, is ensured
Listrium gap 7 effectively obturage.
It is described above, only specific embodiment of the present utility model, but the scope of protection of the utility model is not limited to
In this, any one skilled in the art is in the technical scope that the utility model discloses, the change that can readily occur in
Change or replace, should all cover within the scope of protection of the utility model.Therefore, the scope of protection of the utility model should be with described
Scope of the claims is defined.
Claims (3)
- A kind of 1. turbine nozzle vane listrium seal structure, it is characterised in that：Including the first blade listrium (1), the second blade listrium (2) and obturage piece (3), the first blade listrium (1) with the second leaf The relative side of piece listrium (2) is provided with first and obturages groove (4), the second blade listrium (2) it is relative with the first blade listrium (1) Side is provided with second and obturages groove (5), and first obturages the size and dimension of groove (4) and second to obturage groove (5) identical, and first obturages It is corresponding that groove (5) position on the second blade listrium (2) with second is obturaged in position of the groove (4) on the first blade listrium (1)；First, which obturages groove (4) and second, obturages the wherein one end of groove (5) on the nozzle ring axial direction and is outwardly open, separately One end is closed, and one end of closing is referred to as blind end, and first, which obturages groove (4) and second, obturages groove (5) and form listrium and obturage groove；Obturage both sides of the piece (3) on the nozzle ring axial direction and be separately positioned on first and obturage groove (4) and second and obturage groove (5) in, obturage piece (3) to obturage one end that the blind end of groove is in contact with the listrium be in bending-like, this be in bending-like one end Dogleg section be bending section (6), the both ends of bending section (6) are born against obturages the upper groove surface of groove and lower groove face in the listrium On.
- 2. turbine nozzle vane listrium seal structure according to claim 1, it is characterised in that：First obturages groove (4) It is straight trough to obturage groove (5) with second.
- 3. turbine nozzle vane listrium seal structure according to claim 1, it is characterised in that：Piece (3) is obturaged in institute The length stated on nozzle ring axial direction obturages length of the groove (4) on the nozzle ring axial direction equal to first.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720356918.9U CN206647139U (en) | 2017-04-07 | 2017-04-07 | Turbine nozzle vane listrium seal structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201720356918.9U CN206647139U (en) | 2017-04-07 | 2017-04-07 | Turbine nozzle vane listrium seal structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN206647139U true CN206647139U (en) | 2017-11-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201720356918.9U Active CN206647139U (en) | 2017-04-07 | 2017-04-07 | Turbine nozzle vane listrium seal structure |
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| Country | Link |
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| CN (1) | CN206647139U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412826A (en) * | 2020-10-28 | 2022-04-29 | 中国航发商用航空发动机有限责任公司 | Rotor blade, rotor assembly and gas turbine |
-
2017
- 2017-04-07 CN CN201720356918.9U patent/CN206647139U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114412826A (en) * | 2020-10-28 | 2022-04-29 | 中国航发商用航空发动机有限责任公司 | Rotor blade, rotor assembly and gas turbine |
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