CN204140140U - A kind of clamping ring structure obturaged for gas turbine - Google Patents
A kind of clamping ring structure obturaged for gas turbine Download PDFInfo
- Publication number
- CN204140140U CN204140140U CN201420595682.0U CN201420595682U CN204140140U CN 204140140 U CN204140140 U CN 204140140U CN 201420595682 U CN201420595682 U CN 201420595682U CN 204140140 U CN204140140 U CN 204140140U
- Authority
- CN
- China
- Prior art keywords
- inserted part
- draw
- groove
- clamping ring
- ring
- 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.)
- Active
Links
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a kind of clamping ring structure obturaged for gas turbine, comprise clasp body, clamping ring body is arranged on rotor and obturages between ring and casing, rotor is obturaged annular slot ring and casing be respectively equipped with for installing clamping ring body, clamping ring body is the ring part be made up of high-temperature expansion material, it has first inserted part suitable with draw-in groove, with the second inserted part that draw-in groove is suitable, under normal temperature state, first inserted part and the second inserted part are connected together with draw-in groove Spielpassung respectively, and the gap between the first inserted part and draw-in groove is by turbine cavity and extraneous UNICOM.At high operating temperatures, first inserted part outer ring surface contacts with the high-temperature fuel gas of turbine cavity, expanded by heating, in inflation process, achieve the self-alignment of clamping ring structure, final first inserted part outer ring surface and rotor ring of obturaging is sealed connected together, and is sealed by turbine cavity, prevents high-temperature fuel gas to leak.
Description
Technical field
The utility model relates to gas turbine hermetic seal field, is specifically related to a kind of clamping ring structure obturaged for gas turbine.
Background technique
Use gas turbine aboard, during gas turbine work, inside is in the condition of high temperature, high-temperature high-pressure fuel gas easily leaks, in order to ensure that high-temperature high-pressure fuel gas does not leak, hermetic seal method conventional at present has labyrinth gas seals and brush seal, and labyrinth gas seals structure is simple, low cost of manufacture, but easily wear and tear seal coating, sealing effect is poor; Brush seal overcomes the shortcoming that labyrinth gas seals easily weares and teares, and flow leakage amount is low, but brush seal structure is complicated, and its research and development are higher with manufacture cost.
Summary of the invention
The clamping ring structure that the utility model provides a kind of to be obturaged for gas turbine, good airproof performance, cost are low.
The utility model provides a kind of clamping ring structure obturaged for gas turbine, comprise clamping ring body, clamping ring body is arranged on rotor and obturages between ring and casing, rotor is obturaged annular slot ring and casing be respectively equipped with for installing clamping ring body, clamping ring body is the ring part be made up of high-temperature expansion material, it has first inserted part suitable with draw-in groove, with the second inserted part that draw-in groove is suitable, under normal temperature state, first inserted part and the second inserted part are connected together with draw-in groove Spielpassung respectively, and the gap between the first inserted part and draw-in groove is by turbine cavity and extraneous UNICOM, at high operating temperatures, expand in first inserted part and draw-in groove sealed card is connected together.
Further, clamping ring body is made up of high-temperature expansion material 1Cr11Ni2W2MoV.
Further, the cross section of clamping ring body is L-type.
Further, under normal temperature state, the gap that first inserted part outer ring surface and rotor are obturaged between ring draw-in groove is 0.01 ~ 0.056mm, and the first inserted part inner ring surface and the rotor gap of obturaging between ring draw-in groove are greater than the gap that outer ring surface and rotor are obturaged between ring draw-in groove.
Further, under normal temperature state, the obturage gap of ring draw-in groove snap-fit engagement of the first inserted part outer ring surface and rotor is 0.03mm.
Further, the gap of the second inserted part outer ring surface and casing draw-in groove snap-fit engagement is 0.1 ~ 0.4mm, and the second inserted part inner ring surface and casing are fitted.
Further, under normal temperature state, the gap of the second inserted part outer ring surface and casing draw-in groove snap-fit engagement is 0.25mm.
The beneficial effects of the utility model are: the gap between the first inserted part of clamping ring body and draw-in groove and turbine cavity UNICOM, at high operating temperatures, first inserted part outer ring surface contacts with the high-temperature fuel gas of turbine cavity, expanded by heating, in inflation process, achieve the self-alignment of clamping ring structure, final first inserted part outer ring surface and rotor ring of obturaging is sealed connected together, turbine cavity is sealed, prevents high-temperature fuel gas to leak.
Accompanying drawing explanation
Fig. 1 is the sectional view of the utility model clamping ring structure mounting structure;
Fig. 2 is the partial enlarged drawing A of Fig. 1.
Embodiment
By reference to the accompanying drawings the present invention is described in further detail below by embodiment.
Please refer to Fig. 1 and Fig. 2, present embodiments provide a kind of clamping ring structure obturaged for gas turbine, comprise clamping ring body 1, clamping ring body 1 is made up of high-temperature expansion material, be preferably 1Cr11Ni2W2MoV, its linear expansion coeffcient is as shown in table 1, also can be replaced the material that linear expansion coeffcient is close with 1Cr11Ni2W2MoV in other embodiments.
| 1 | θ/℃ | α/10-6℃-1 |
| 2 | 20～100 | 9.3 |
| 3 | 20～200 | 10.3 |
| 4 | 20～300 | 10.8 |
| 5 | 20～400 | 11.3 |
| 6 | 20～450 | 11.5 |
| 7 | 20～500 | 11.7 |
| 8 | 20～600 | 12.2 |
Table 1
Clamping ring body 1 is arranged on rotor and obturages between ring 2 and casing 3, turbine cavity 4 separated with the external world, rotor is obturaged on ring 2 and casing 3 and is respectively equipped with annular slot 21 and annular slot 31, on cross section, draw-in groove 21 and all U-shaped draw-in groove of draw-in groove 31, and two draw-in grooves are mutually vertical.Accordingly, clamping ring structure clamping ring body 1 for cross section be the ring part of L-type, clamping ring structure clamping ring body 1 is provided with the first inserted part 1a and the second inserted part 1b, the annular slot 21 of obturage with rotor respectively ring 2 and casing 3 and annular slot 31 clamping.
Gas turbine is in idle situation, be in normal temperature environment, first inserted part 1a and rotor are obturaged the gap clamping of ring 2 draw-in groove 21, first inserted part 1a outer ring surface be 0.01 ~ 0.056mm with the obturage gap of ring 2 draw-in groove 21 of rotor, be preferably 0.03mm, first inserted part 1a inner ring surface is greater than the first inserted part 1a outer ring surface obturages the gap of ring 2 draw-in groove 21 with rotor with the obturage gap of ring 2 draw-in groove 21 of rotor, clamping ring structure can moved radially, be convenient to centering, and the first inserted part 1a inner ring surface under the high temperature conditions is first sealed with the obturage gap of ring 2 draw-in groove 21 of rotor.Inside and outside first inserted part 1a, the gap of anchor ring is by turbine cavity 4 and extraneous UNICOM.
Second inserted part 1b and the gap clamping of casing 3 draw-in groove 31, casing 3 draw-in groove 31 is combined by casing 3 and nut backing plate, the gap of the second inserted part 1b outer ring surface and draw-in groove 31 is 0.1 ~ 0.4mm, is preferably 0.25mm, the gap namely between the second inserted part 1b and nut backing plate; Second inserted part 1b inner ring surface and draw-in groove 31 are fitted.The setting party in gap the installation of clamping ring structure, under the action of the forces of the wind, clamping ring body 1 axially can not move, therefore very close to each otherly in draw-in groove 31 makes turbine cavity and extraneous UNICOM.
Under gas turbine working state, combustion gas vigorous combustion in turbine cavity 4, cavity is in high temperature and high pressure environment, high-temperature fuel gas enters in the gap that the first inserted part 1a and rotor obturage between ring 2 draw-in groove 21, first inserted part 1a expanded by heating, in inflation process, achieve the self-alignment of clamping ring structure, final first inserted part 1a outer ring surface expands and has filled up the gap that the first inserted part 1a outer ring surface and rotor obturage between ring 2 draw-in groove 21, first inserted part 1a is sealedly connected on and obturages in the draw-in groove 21 of ring 2 with rotor, turbine cavity 4 is isolated from the outside, prevent leaking of high-temperature fuel gas.
Above content is in conjunction with concrete mode of execution further description made for the present invention, can not assert that specific embodiment of the invention is confined to these explanations.For general technical staff of the technical field of the invention, without departing from the inventive concept of the premise, some simple deduction or replace can also be made.
Claims (7)
1. the clamping ring structure obturaged for gas turbine, it is characterized in that, comprise clamping ring body (1), described clamping ring body (1) is arranged on rotor and obturages between ring (2) and casing (3), described rotor is obturaged the annular slot (21 ring (2) and casing (3) be respectively equipped with for installing clamping ring body (1), 31), described clamping ring body (1) is the ring part be made up of high-temperature expansion material, it has first inserted part (1a) suitable with draw-in groove (21), with the second inserted part (1b) that draw-in groove (31) is suitable, under normal temperature state, first inserted part (1a) and the second inserted part (1b) respectively with draw-in groove (21, 31) Spielpassung is connected together, and the gap between the first inserted part (1a) and draw-in groove (21) is by turbine cavity (4) and extraneous UNICOM, at high operating temperatures, expand in first inserted part (1a) and draw-in groove (21) sealed card is connected together.
2. clamping ring structure as claimed in claim 1, it is characterized in that, described clamping ring body (1) is made up of high-temperature expansion material 1Cr11Ni2W2MoV.
3. clamping ring structure as claimed in claim 2, it is characterized in that, the cross section of described clamping ring body (1) is L-type.
4. clamping ring structure as claimed in claim 3, it is characterized in that, under normal temperature state, described first inserted part (1a) outer ring surface and the rotor gap of obturaging between ring (2) draw-in groove (21) is 0.01 ~ 0.056mm, and described first inserted part (1a) inner ring surface and the rotor gap of obturaging between ring (2) draw-in groove (21) is greater than the gap that outer ring surface and rotor are obturaged between ring (2) draw-in groove (21).
5. clamping ring structure as claimed in claim 4, is characterized in that, under normal temperature state, the obturage gap of ring (2) draw-in groove (21) snap-fit engagement of described first inserted part (1a) outer ring surface and rotor is 0.03mm.
6. clamping ring structure as claimed in claim 5, it is characterized in that, under normal temperature state, the gap of described second inserted part (1b) outer ring surface and casing (3) draw-in groove (31) snap-fit engagement is 0.1 ~ 0.4mm, and described second inserted part (1b) inner ring surface and casing (3) are fitted.
7. clamping ring structure as claimed in claim 6, it is characterized in that, under normal temperature state, the gap of described second inserted part (1b) outer ring surface and casing (3) draw-in groove (31) snap-fit engagement is 0.25mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420595682.0U CN204140140U (en) | 2014-10-15 | 2014-10-15 | A kind of clamping ring structure obturaged for gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420595682.0U CN204140140U (en) | 2014-10-15 | 2014-10-15 | A kind of clamping ring structure obturaged for gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204140140U true CN204140140U (en) | 2015-02-04 |
Family
ID=52416833
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201420595682.0U Active CN204140140U (en) | 2014-10-15 | 2014-10-15 | A kind of clamping ring structure obturaged for gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN204140140U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114576008A (en) * | 2020-11-30 | 2022-06-03 | 中国航发商用航空发动机有限责任公司 | Aeroengine casing and aeroengine |
| CN114576008B (en) * | 2020-11-30 | 2024-06-04 | 中国航发商用航空发动机有限责任公司 | Aeroengine casing and aeroengine |
-
2014
- 2014-10-15 CN CN201420595682.0U patent/CN204140140U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114576008A (en) * | 2020-11-30 | 2022-06-03 | 中国航发商用航空发动机有限责任公司 | Aeroengine casing and aeroengine |
| CN114576008B (en) * | 2020-11-30 | 2024-06-04 | 中国航发商用航空发动机有限责任公司 | Aeroengine casing and aeroengine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN203686121U (en) | Sealing ring | |
| CN206738156U (en) | A kind of new No leakage roots blower sealing device | |
| CN103016741A (en) | Mixing machine shaft end sealing device | |
| CN204164340U (en) | Built-up piston seal arrangement | |
| CN204140140U (en) | A kind of clamping ring structure obturaged for gas turbine | |
| CN203285984U (en) | Sealing ring of internal water cooling | |
| CN203718211U (en) | Series connection sealing connecting device | |
| CN201851393U (en) | Shaft sealing structure of centrifugal fan | |
| CN208268410U (en) | A kind of dust-proof outside framework oil seal | |
| CN201386690Y (en) | Sealing device for vertical condensate pump | |
| CN204729135U (en) | A kind of nozzle box's device of steam turbine and steam turbine | |
| CN203374781U (en) | Sealing ring of motor of dust collector | |
| CN210290749U (en) | Large-scale transmission slip ring based on end face dynamic seal | |
| CN207393425U (en) | A kind of Compressor Piston Ring support device | |
| CN203686132U (en) | Plastic mechanical oil seal | |
| CN203948678U (en) | The box-like sealing configuration of a kind of valve sets | |
| CN203395185U (en) | Air pressure closed type mechanical seal | |
| CN205401461U (en) | Shaft pivot bearing unloads die mould sealing washer | |
| CN202108640U (en) | Sealing device of water turbine | |
| CN201521641U (en) | Efficient carbon ring sealing device | |
| CN204004412U (en) | A kind of radially dynamic adjustable contact type sealing device for axle head | |
| CN215634974U (en) | Double-lip framework oil seal | |
| CN205331414U (en) | Valve seal ring | |
| CN201944277U (en) | Sealing device for high-pressure and high-speed reactor | |
| CN202501007U (en) | Novel rubber sealing ring |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP01 | Change in the name or title of a patent holder |
Address after: 412002 Dong Jia Duan, Lusong District, Zhuzhou City, Hunan Province Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jia Duan, Lusong District, Zhuzhou City, Hunan Province Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
|
| CP01 | Change in the name or title of a patent holder |