CN204402572U - A kind of gas turbine turbine stator blade seal ring supporting structure - Google Patents
A kind of gas turbine turbine stator blade seal ring supporting structure Download PDFInfo
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- CN204402572U CN204402572U CN201420872092.8U CN201420872092U CN204402572U CN 204402572 U CN204402572 U CN 204402572U CN 201420872092 U CN201420872092 U CN 201420872092U CN 204402572 U CN204402572 U CN 204402572U
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- turbine
- stator blade
- seal ring
- blade seal
- turbine stator
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Abstract
A kind of gas turbine turbine stator blade seal ring supporting structure, relates to gas turbine structure design.Turbine stator blade seal ring supporting structure comprises multiple supporting part, and each supporting part contains stay bolt, pad, turbine hold annular distance, turbine stator blade hole and turbine stator blade seal ring tapped hole; Stay bolt holds annular distance and turbine stator blade hole through turbine, and the screw thread of its end and the corresponding threaded holes of turbine stator blade seal ring close.Multiple supporting part is circumferentially evenly arranged, and is arranged symmetrically with relative to the vertical plane of the radial and axial composition of combustion engine turbine.By adjusting the degree of depth of this matching thread, stator blade seal ring can be realized and hold the concentric of ring with turbine.The gravity of turbine stator blade seal ring is delivered to turbine by stay bolt and holds on ring, and turbine stator blade does not bear the gravity of stator blade seal ring, and adjacent stator blade can free expansion, and stator blade surface of contact does not produce supplementary contact stress.The utility model structure is simple, adjustment and easy accessibility, thus ensures that gas turbine reliably, stably works.
Description
Technical field
The utility model relates to gas turbine mechanical structural design, belongs to gas turbine structure design field.
Background technique
In gas turbine work, because in turbine, fuel gas temperature is high, adopt and introduce cooled gas mode from other positions, turbine stator and rotor part are cooled.In turbine stator blade lower end, turbine stator blade seal ring is installed, the cooled gas flowed out in turbine stator blade is guided and enters the turbine rotor wheel disc dish chamber of specifying, for cooling turbine rotor disk, can effectively reduce turbine rotor disk temperature, improve cooled gas utilization ratio, improve efficiency and the reliability of unit.When turbine stator is installed, it is concentric that all stator parts circumferentially need ensure to hold ring with turbine; During general assembly, only need ensure that the ring security of operation that can ensure turbine stator part and rotor part concentric on rotor held by turbine, avoid stator part to scratch mutually with rotor part, ensure security of operation.
The mounting and adjusting structure of traditional industry gas turbine turbine stator blade seal ring comprises square toes pin 9, eccentric bushing 10, lock banking stop 11 and special bolts 12; Square toes pin 9 and turbine stator blade lower end fit depressions, by rotating eccentricity cover 10, drive the square toes pin be arranged in the groove of turbine stator blade 2 lower end, the position of adjustable turbine stator blade seal ring 3, realizing turbine stator blade seal ring and turbine, to hold ring concentric, after adjustment completes, the position lock banking stop of eccentric bushing is locked, by special bolts 12, lock banking stop 11 is tightened on turbine stator blade seal ring 3, adopt welding manner (as shown in Figure 2) again) position of special bolts and lock banking stop is locked, prevent from loosening, thus realize the location of turbine stator blade seal ring.This adjust structure is arranged on multiple stator blade lower end, and the relatively many and mounting and adjusting trouble of part, need remove comparatively difficulty (see Fig. 1 and Fig. 2) by welding portion during dismounting.Because turbine stator blade seal ring directly contacts with part turbine stator blade, its gravity is born by turbine stator blade, assemblage gap between the adjacent stator blade of part can be caused to disappear, operationally because the expanded by heating of stator blade can bring the stress of surface of contact to increase, reduce the life-span of stator blade.
Model utility content
The purpose of this utility model is to provide a kind of gas turbine turbine stator blade seal ring supporting structure, the adjustment of industry gas turbine turbine stator blade seal ring and dismounting inconvenience problem can be solved preferably, improve the functional reliability of gas turbine turbine stator blade seal ring structure, stability and life-span.
The technical solution of the utility model is as follows:
A kind of gas turbine turbine stator blade seal ring supporting structure, it is characterized in that, this supporting structure comprises the multiple supporting parts holding ring circumferential directions along turbine, and each supporting part contains stay bolt, pad, turbine hold annular distance, turbine stator blade hole and turbine stator blade seal ring bolt hole; Annular distance held by described turbine, the center line of turbine stator blade hole and turbine stator blade seal ring bolt hole is positioned on the same radial line of combustion engine turbine; Described stay bolt matches with turbine stator blade seal ring bolt hole hold the turbine stator blade hole on annular distance and turbine stator blade successively through the turbine turbine held on ring after.
In described technological scheme, described multiple supporting parts are circumferentially evenly arranged, and are arranged symmetrically with relative to the vertical plane of the radial and axial composition of combustion engine turbine.
The utility model compared with prior art, have the following advantages and beneficial effect: 1. in gas turbine turbine stator blade seal ring supporting structure provided by the utility model, stay bolt center line is on combustion engine turbine radial line, the gravity of turbine stator blade seal ring is delivered to turbine by stay bolt and holds on ring, turbine stator blade does not bear the gravity of stator blade seal ring, adjacent stator blade can free expansion, stator blade surface of contact does not produce supplementary contact stress, when gas turbine works, expansion and the contraction of turbine stator blade seal ring are directly carried out along stay bolt in combustion engine turbine radial direction, ensure that ring held by turbine stator blade seal ring and turbine concentric all the time, thus ensure that gas turbine is more stable, reliably run.2. this supporting structure have that structure is simple, the advantage such as adjustment and easy accessibility.
Accompanying drawing explanation
Fig. 1 is existing gas turbine turbine stator blade seal ring supporting structure schematic three dimensional views.
Fig. 2 is existing gas turbine turbine stator blade seal ring supporting structure sectional view.
Fig. 3 is the circumferential distribution schematic diagram of the gas turbine turbine stator blade seal ring supporting structure that the utility model provides.
Fig. 4 is the gas turbine turbine stator blade seal ring supporting structure sectional view that the utility model provides.
List of parts: ring held by 1-turbine; 2-turbine stator blade; 3-turbine stator blade seal ring; 4-stay bolt; 5-pad; Annular distance held by 6-turbine; 7-turbine stator blade hole; 8-turbine stator blade seal ring tapped hole; 9-square toes pin; 10-eccentric bushing; 11-lock banking stop; 12-special bolts; The plane of the vertical radial and axial composition of 13-turbine; 14-combustion engine turbine radial line.
Embodiment
Below in conjunction with accompanying drawing, structure of the present utility model, principle and working procedure are described further.
As the turbine stator blade seal ring supporting structure schematic diagram that Fig. 3, Fig. 4 provide for the utility model, this supporting structure comprises the multiple supporting parts holding ring circumferential directions along turbine, and each supporting part contains stay bolt 4, pad 5, turbine hold annular distance 6, turbine stator blade hole 7 and turbine stator blade seal ring bolt hole 8; Annular distance 6 held by described turbine, the center line of turbine stator blade hole 7 and turbine stator blade seal ring bolt hole 8 is positioned on the same radial line 14 of combustion engine turbine; The lower end of stay bolt 4 is provided with screw thread, stay bolt 4 and turbine are held between ring 1 and are provided with pad 5, after this stay bolt 4 holds the turbine stator blade hole 7 on annular distance 6 and turbine stator blade 2 through the turbine turbine held on ring 1 successively, match with the turbine stator blade seal ring bolt hole 8 be arranged on turbine stator blade seal ring, realize screw-thread fit to install, by adjusting the degree of depth of this matching thread, realizing turbine stator blade seal ring 3 and holding the concentric of ring 1 with turbine.Turbine holds annular distance 6, turbine stator blade hole 7 and turbine stator blade seal ring tapped hole 8 on same combustion engine turbine radial line 14, turbine stator blade seal ring 3 can be made so radially to expand when expanded by heating, ensure that turbine stator blade seal ring 3 and turbine are held when ring 1 works concentric all the time.The gravity of turbine stator blade seal ring 3 is delivered to turbine by stay bolt 4 and holds on ring 1, and turbine stator blade 2 does not bear the gravity of turbine stator blade seal ring 3.Evenly being delivered to turbine in order to make the gravity of turbine stator blade seal ring 3 better by stay bolt 4 holds on ring 1, and multiple supporting structure should along the circumferential direction be evenly arranged, and is arranged symmetrically with relative to the vertical plane 13 of the radial and axial composition of combustion engine turbine.
Claims (2)
1. a gas turbine turbine stator blade seal ring supporting structure, it is characterized in that, this supporting structure comprises the multiple supporting parts holding ring circumferential directions along turbine, and each supporting part contains stay bolt (4), pad (5), turbine hold annular distance (6), turbine stator blade hole (7) and turbine stator blade seal ring bolt hole (8); Annular distance (6) held by described turbine, the center line of turbine stator blade hole (7) and turbine stator blade seal ring bolt hole (8) is positioned on the same radial line (14) of combustion engine turbine; Match with turbine stator blade seal ring bolt hole (8) afterwards in the turbine stator blade hole (7) that described stay bolt (4) is held on annular distance (6) and turbine stator blade (2) through the turbine turbine held on ring (1) successively.
2. a kind of gas turbine turbine stator blade seal ring supporting structure as claimed in claim 1, it is characterized in that, multiple supporting part is circumferentially evenly arranged, and is arranged symmetrically with relative to the vertical plane (13) of the radial and axial composition of combustion engine turbine.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420872092.8U CN204402572U (en) | 2014-12-31 | 2014-12-31 | A kind of gas turbine turbine stator blade seal ring supporting structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420872092.8U CN204402572U (en) | 2014-12-31 | 2014-12-31 | A kind of gas turbine turbine stator blade seal ring supporting structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204402572U true CN204402572U (en) | 2015-06-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420872092.8U Active CN204402572U (en) | 2014-12-31 | 2014-12-31 | A kind of gas turbine turbine stator blade seal ring supporting structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN204402572U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107542501A (en) * | 2017-09-28 | 2018-01-05 | 中国航发动力股份有限公司 | A kind of flue gas turbine expander can adjust diffusion segment structure |
| CN112761734A (en) * | 2021-04-07 | 2021-05-07 | 中国联合重型燃气轮机技术有限公司 | Adjusting device for a stationary blade carrier ring of a gas turbine and gas turbine |
-
2014
- 2014-12-31 CN CN201420872092.8U patent/CN204402572U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107542501A (en) * | 2017-09-28 | 2018-01-05 | 中国航发动力股份有限公司 | A kind of flue gas turbine expander can adjust diffusion segment structure |
| CN107542501B (en) * | 2017-09-28 | 2019-07-05 | 中国航发动力股份有限公司 | A kind of adjustable diffusion segment structure of flue gas turbine expander |
| CN112761734A (en) * | 2021-04-07 | 2021-05-07 | 中国联合重型燃气轮机技术有限公司 | Adjusting device for a stationary blade carrier ring of a gas turbine and gas turbine |
| CN112761734B (en) * | 2021-04-07 | 2021-07-20 | 中国联合重型燃气轮机技术有限公司 | Adjusting device for a stationary blade carrier ring of a gas turbine and gas turbine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Supporting structure for turbine static blade sealing ring of gas turbine Effective date of registration: 20161104 Granted publication date: 20150617 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150617 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |