CN201778840U - Gas-tight structure of turbine spindle - Google Patents
Gas-tight structure of turbine spindle Download PDFInfo
- Publication number
- CN201778840U CN201778840U CN201020524792XU CN201020524792U CN201778840U CN 201778840 U CN201778840 U CN 201778840U CN 201020524792X U CN201020524792X U CN 201020524792XU CN 201020524792 U CN201020524792 U CN 201020524792U CN 201778840 U CN201778840 U CN 201778840U
- Authority
- CN
- China
- Prior art keywords
- gas
- main shaft
- air
- spindle
- tight
- 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.)
- Expired - Fee Related
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model discloses a gas-tight structure of a turbine spindle with good leak tightness and high safety. The gas-tight structure is arranged between a spindle and a housing, and comprises at least two sealing rings which are arranged at intervals along the axial direction of the spindle and are in interference fit with the spindle, more than eight sealing rings are embedded in a gas-tight body connected with the housing, a step is arranged on the gas-tight body, a retaining ring is arranged at the step to support the gas-tight body on the spindle, the leak tightness of the conventional gas-tight structure is improved, the leakage rate is small, the safety is good, and the gas-tight structure is especially applied to blast furnace coal gas excess pressure turbines.
Description
Technical field
The utility model relates to a kind of air seal structure, especially a kind of turbine engine main shaft air seal structure.
Background technique
The main shaft air seal structure of existing turbine engine generally adopts labyrinth seal, and it comprises seal ring, and seal ring is provided with a plurality of ring packing teeth, and seal ring is fixed on the casing.Existing labyrinth seal structure may produce gas explosion because of leakage when being applied to the blast furnace gas turbine engine, have potential safety hazard.
The model utility content
In order to overcome the deficiency of existing turbine engine main shaft air seal structure Security, technical problem to be solved in the utility model provides a kind of better tightness, the turbine engine main shaft air seal structure that Security is higher.
The technological scheme that its technical problem that solves the utility model adopts is: turbine engine main shaft air seal structure, air seal structure is arranged between main shaft and the casing, described air seal structure comprise at least two along the main shaft axially spaced-apart that be provided with the seal ring main shaft interference fit, described each seal ring is embedded in the air sealing, and air sealing is connected with casing.
Described seal ring has more than 8.
Described air sealing is provided with step, and the step place is provided with baffle ring air sealing is supported on the main shaft.
The beneficial effects of the utility model are: sealability has improvement than existing structure, and leakage rate is minimum, and Security is good.
Description of drawings
Fig. 1 is the schematic representation of existing turbine engine main shaft air seal structure.
Fig. 2 is the schematic representation of the utility model turbine engine main shaft air seal structure.
Be labeled as 1-main shaft, 2-casing, 3-seal, 4-seal ring, 5-air sealing, 6-baffle ring, 51-step among the figure.
Embodiment
Below in conjunction with accompanying drawing the utility model is further specified.
As shown in Figure 1, existing sealing configuration realizes that for utilizing the seal with a plurality of annular tooth it is through-type labyrinth seal to sealing of spindles.
As shown in Figure 2, turbine engine main shaft air seal structure of the present utility model, air seal structure is arranged between main shaft 1 and the casing 2, described air seal structure comprise at least two along main shaft 1 axially spaced-apart that be provided with seal ring 4 main shaft 1 interference fit, described each seal ring 4 is embedded in the air sealing 5, air sealing 5 is connected with casing 2, like this, formed a diplarthrous labyrinth seal between the main shaft 1 and seal ring 4 close fit, the two and air sealing 5, the penetration effect of air-flow reduces, leakage rate is minimum, and Security improves greatly, simultaneously, the processing of seal ring 4 is simple, longer service life.
For further improving Security, reduce leakage rate, described seal ring 4 preferably is provided with more than 8, for example 10.
Usually, the described seal ring 4 preferred carbon bodies that adopt, as the dynamic pressure sealing, its sealing effect is better.
For ease of assembling and positioning, can be provided with step 51 by described air sealing 5, step 51 places are provided with baffle ring 6 air sealing 5 are supported on the main shaft 1.
Claims (3)
1. turbine engine main shaft air seal structure, air seal structure is arranged between main shaft (1) and the casing (2), it is characterized in that: described air seal structure comprise at least two along main shaft (1) axially spaced-apart that be provided with seal ring (4) main shaft (1) interference fit, described each seal ring (4) is embedded in the air sealing (5), and air sealing (5) is connected with casing (2).
2. turbine engine main shaft air seal structure as claimed in claim 1 is characterized in that: described seal ring (4) has more than 8.
3. turbine engine main shaft air seal structure as claimed in claim 1 or 2 is characterized in that: described air sealing (5) is provided with step (51), and step (51) is located to be provided with baffle ring (6) air sealing (5) is supported on the main shaft (1).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020524792XU CN201778840U (en) | 2010-05-19 | 2010-09-10 | Gas-tight structure of turbine spindle |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201020195817 | 2010-05-19 | ||
| CN201020195817.6 | 2010-05-19 | ||
| CN201020524792XU CN201778840U (en) | 2010-05-19 | 2010-09-10 | Gas-tight structure of turbine spindle |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201778840U true CN201778840U (en) | 2011-03-30 |
Family
ID=43792053
Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201020524792XU Expired - Fee Related CN201778840U (en) | 2010-05-19 | 2010-09-10 | Gas-tight structure of turbine spindle |
| CN2010102781869A Pending CN102251815A (en) | 2010-05-19 | 2010-09-10 | Air sealing structure for main shaft of turbomachine |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010102781869A Pending CN102251815A (en) | 2010-05-19 | 2010-09-10 | Air sealing structure for main shaft of turbomachine |
Country Status (1)
| Country | Link |
|---|---|
| CN (2) | CN201778840U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102363821A (en) * | 2011-11-02 | 2012-02-29 | 思安新能源股份有限公司 | High speed blast furnace gas pressure turbine |
-
2010
- 2010-09-10 CN CN201020524792XU patent/CN201778840U/en not_active Expired - Fee Related
- 2010-09-10 CN CN2010102781869A patent/CN102251815A/en active Pending
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102363821A (en) * | 2011-11-02 | 2012-02-29 | 思安新能源股份有限公司 | High speed blast furnace gas pressure turbine |
| CN102363821B (en) * | 2011-11-02 | 2014-01-29 | 思安新能源股份有限公司 | High speed blast furnace gas pressure turbine |
Also Published As
| Publication number | Publication date |
|---|---|
| CN102251815A (en) | 2011-11-23 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20110330 Termination date: 20130910 |