CN202266301U - Turbine machine and turbine engine with same - Google Patents
Turbine machine and turbine engine with same Download PDFInfo
- Publication number
- CN202266301U CN202266301U CN 201120314675 CN201120314675U CN202266301U CN 202266301 U CN202266301 U CN 202266301U CN 201120314675 CN201120314675 CN 201120314675 CN 201120314675 U CN201120314675 U CN 201120314675U CN 202266301 U CN202266301 U CN 202266301U
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- stator
- turbine
- cavity
- turbine disk
- guide plate
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Abstract
The utility model provides a turbine machine and a turbine engine with the same. The turbine machine comprises a turbine plate (3) and a stator (4) adjacent to the turbine plate (3), a cavity is formed between the turbine plate (3) and the stator (4), and a flow guide plate (2) is arranged in the cavity between the turbine plate (3) and the stator (4) to divide the cavity into a first cavity (1) and a second cavity (9). The flow guide plate (2) is fixed on the stator (4), a cooling air inlet (6) is arranged on the lateral wall of the stator (4), a rotor (11) is positioned on the turbine plate (3), and an air flow outlet is arranged between the rotor (11) and the stator (4). The flow guide plate is arranged in the turbine cavity so as to enable circulation area of cooling air to be greatly reduced and greatly improve utilization efficiency of the cooling air. The flow guide plate of the turbine plate enables the cooling air to approximately flow along with the surface of the turbine plate, thereby fully taking away heat on plate surface of the turbine plate and improving cooling effect.
Description
Technical field
The utility model relates to engine art, especially, relates to a kind of turbo machine with guide plate of cooling and the effect of obturaging.In addition, the utility model also relates to a kind of turbogenerator that comprises above-mentioned turbo machine.
Background technique
Along with improving constantly of aeroengine thrust weight ratio or power to weight ratio, its hot-end component has born higher temperature and bigger load.For life-span and the reliability that improves aeroengine, the operating temperature that reduces hot-end component is most important.The turbine disk is the vital part of aeroengine, is bearing the load of harsh heat and machinery, the operating conditions very severe.For guaranteeing the turbine disk safe and reliable work in the lifetime that requires, under the situation of reasonably select material,, utilize cooling air to take away that blade is passed in combustion gas and pass to the heat of the turbine disk through blade mainly through the cooling of the turbine disk.
At present, the cooling of the turbine disk adopts the cooling air turbine disk of directly flowing through to take away heat basically.Yet because turbine disk cavity space is bigger, the turbine disk is folding shape, and cooled gas flows to the air outlet after getting into turbine disk chamber straight.Therefore, the gas flow rate at turbine disk knuckle place is very slow, forms the relative dead angle of cooling easily, does not allow to be cooled.Therefore, the cooling effect utilization ratio relatively poor, cooled gas of the type of cooling of the turbine disk is very low at present.
The model utility content
The utility model purpose is to provide a kind of turbo machine, to solve the technical problem that cooling effect is relatively poor, the cooled gas utilization ratio is not high of the turbine disk in the existing technology turbo machine.
For realizing above-mentioned purpose; The utility model provides a kind of turbo machine, comprises the turbine disk and the stator adjacent with the turbine disk, is formed with cavity between the turbine disk and the stator; One guide plate is set, cavity is divided into first cavity and second cavity in the cavity between the turbine disk and stator; Guide plate is fixed on the stator, on the stator sidewall, is provided with the cooled gas entry port; The turbine disk is provided with rotor; Offer flow outlet between rotor and the stator.
Further, guide plate is provided with the exhaust port that first cavity and second cavity are connected.
Further, be provided with stream between guide plate and the stator towards turbine disk core wheel place.
Further, be processed with bolt hole on the guide plate, guide plate is through being bolted on the stator.
Further, bolt is processed into hollow structure, forms the cooled gas entry port.
Further, the cooled gas entry port is located on the sidewall of stator, and connects with stream.
The utility model also provides a kind of turbogenerator, and it is that turbo machine is installed in turbogenerator, and turbo machine is above-mentioned turbo machine.
The beneficial effect of the utility model is: because turbo machine has adopted in the turbine cavity guide plate is set, make cooled gas greatly reduce in the circulation area in turbine disk chamber, improved the utilization ratio of cooled gas greatly; Turbine disk guide plate makes cooled gas roughly along turbine disk Surface runoff, fully takes away the heat of turbine disk card, improves cooling effect.
Except top described purpose, feature and advantage, the utility model also has other purpose, feature and advantage.To do further detailed explanation to the utility model with reference to figure below.
Description of drawings
The accompanying drawing that constitutes the application's a part is used to provide the further understanding to the utility model, and illustrative examples of the utility model and explanation thereof are used to explain the utility model, do not constitute the improper qualification to the utility model.In the accompanying drawings:
Fig. 1 is the structural representation of the utility model preferred embodiment;
Fig. 2 is the structural representation of the turbine disk of the utility model preferred embodiment; And
Fig. 3 is another embodiment's of the utility model a structural representation.
Embodiment
Embodiment to the utility model is elaborated below in conjunction with accompanying drawing, but the multitude of different ways that the utility model can be defined by the claims and cover is implemented.
Referring to Fig. 1 and Fig. 2, the turbo machine of the utility model comprises the turbine disk 3, turbine blade 10, guide plate 2 and stator 4.The sectional shape of this turbine disk 3 roughly is folding shape, and first end of the turbine disk 3 is connected with first end of rotor 11, and second end of rotor 11 connects turbine blade 10.Form a turbine disk chamber 1 between the relative stator 4 of the turbine disk and the turbine disk 3.
The turbine disk 3 comprise first section 31 of being connected with rotor 11, by first section 31 extend and with second section 32 of first section 31 approximate vertical and by second section 32 extend and with the 3rd section 33, the three sections 33 of first section 31 almost parallel be the core wheel place of the turbine disk.
This guide plate 2 is arranged between the adjacent stator 4 of the turbine disk 3 and the turbine disk 3, thereby is divided into first cavity 1 and second cavity 9 to the cavity between the turbine disk 3 and the stator 4.Be processed with bolt hole on the guide plate 2, guide plate 2 passes bolt hole through bolt 61 and is fixed on the stator 4.Be provided with Sealing between this bolt retaining head and the guide plate 2; The sealing part makes cooled gas get into behind the turbine disk cavity not can be directly to get into first cavity 1 from the space of bolt hole; Make at first the flow through core wheel place in turbine disk chamber 1 of cooled gas, to reach the effect in the highest core wheel zone of abundant chilling temperature; On the other hand; The cooled gas that Sealing also prevents to flow to the turbine disk 3 one sides is directly counter from the space of bolt hole again behind the turbine disk chamber 1 that just gets into the turbine disk 3 one sides to flow outflow; Promptly form minor loop; To prevent the cooled gas turbine disk 3 of can not all flowing through, realize the cooling of the whole turbine disk 3, reduce the utilization ratio of cooled gas.
The sectional shape of this guide plate 2 is close with the shape of the turbine disk 3, and is provided with near the turbine disk 3.Like this; The gap that forms between the guide plate 2 and the turbine disk 3 makes when cooled gas flows between the guide plate 2 and the turbine disk 3 about equally, guarantees that the thickness of air-flow is basic identical; Thereby guaranteed the cooled gas turbine disk 3 of at the uniform velocity flowing through; And can not form the dead angle that cooled gas flows in the corner of the turbine disk 3, make the turbine disk 3 coolings evenly, the utilization ratio of cooled gas improves greatly.
Be set to the narrow flow path 21 towards core wheel place, turbine disk chamber between the adjacent stator 4 of the guide plate 2 and the turbine disk, this stream guarantees the flow direction after cooled gas gets into turbine disk chamber, and cooled gas flows to core wheel place, turbine disk chamber earlier core wheel is cooled off.Because the highest, the mechanical load of the temperature at core wheel place is maximum in the turbine disk, environment is the most abominable, at first the core wheel of cooling turbine dish 3 zone can guarantee whole cooling effect.
Be used for the bolt 61 that guide plate 2 is fixed on the stator 4 is processed into hollow structure, the interior bone in the bolt 61 of this hollow is as cooled gas entry port 6.Bolt 61 is used for forms the cooled gas entry port, can reduce the hole of offering at the adjacent stator 4 of the turbine disk, like this, it is dual-purpose that being used on stator 4 and the guide plate 2 passed bolt hole one hole of bolt 61, can improve the mechanical strength of the adjacent stator 4 of the turbine disk.
Leave flow outlet 5 between rotor 11 and the stator 4.This flow outlet 5 is set to the labyrinth outlet, and promptly the flange of rotor 11 gos deep in the groove of stator 4.Like this, flow outlet 5 makes cooled gas discharge first cavity 1 in the turbine disk 3 backs of flowing through.When the cooled gas of not supplying with or supplying with on a small quantity, the air pressure in first cavity 1 can be less than air pressure outside the chamber, and at this moment hot gas can instead flow in first cavity 1 outside the chamber, and the labyrinth outlet is set, and can effectively prevent the anti-stream of hot gas.Simultaneously; The labyrinth flow outlet also can improve the utilization ratio of cooled gas, after promptly cooled gas gets in first cavity 1; Because little, the path length of bore of flow outlet 5; Make cooled gas not flow out fast, in turbine disk chamber 1, form overstocking to a certain degree, make that cooling effect is better, the cooled gas utilization ratio is higher.
Referring to Fig. 3, as other mode of execution, this cooled gas entry port 6 can be opened on the sidewall of stator 4 and narrow flow path 21 position adjacent, and connects with narrow flow path 21.Offer cooled gas entry port 6 separately, can more conveniently operate,, can not influence the fixedly bolt 61 of guide plate 2, can guarantee that bolt 61 and guide plate 2 do not become flexible at switch or when adjusting cooled gas air-flow big or small.
The utility model also provides a kind of motor, and above-mentioned turbo machine is installed in this motor.This motor can be installed on the aircraft, and on other practical machine.
The preferred embodiment that the above is merely the utility model is not limited to the utility model, and for a person skilled in the art, the utility model can have various changes and variation.All within the spirit and principle of the utility model, any modification of being done, be equal to replacement, improvement etc., all should be included within the protection domain of the utility model.
Claims (7)
1. a turbo machine comprises the turbine disk (3) and the stator (4) adjacent with the said turbine disk (3), is formed with cavity between the said turbine disk (3) and the said stator (4),
It is characterized in that, in the cavity between the said turbine disk (3) and said stator (4) guide plate (2) is set, said cavity is divided into first cavity (1) and second cavity (9);
Said guide plate (2) is fixed on the said stator (4), on said stator (4) sidewall, is provided with cooled gas entry port (6);
The said turbine disk (3) is provided with rotor (11);
Offer flow outlet (5) between said rotor (11) and the said stator (4).
2. turbo machine according to claim 1 is characterized in that, said guide plate (2) is provided with the exhaust port (7,8) that said first cavity (1) and said second cavity (9) are connected.
3. turbo machine according to claim 1 is characterized in that, is provided with the stream (21) towards turbine disk core wheel place between said guide plate (2) and the said stator (4).
4. turbo machine according to claim 3 is characterized in that, said guide plate is processed with bolt hole on (2), and said guide plate (2) is fixed on the said stator (4) through bolt (61).
5. turbo machine according to claim 4 is characterized in that, said bolt (61) is processed into hollow structure, forms said cooled gas entry port (6).
6. turbo machine according to claim 3 is characterized in that, said cooled gas entry port (6) is located on the sidewall of said stator (4), and connects with said stream (21).
7. a turbogenerator is equipped with turbo machine in turbogenerator, it is characterized in that, said turbo machine is any described turbo machine in the claim 1 to 6.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120314675 CN202266301U (en) | 2011-08-24 | 2011-08-24 | Turbine machine and turbine engine with same |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201120314675 CN202266301U (en) | 2011-08-24 | 2011-08-24 | Turbine machine and turbine engine with same |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202266301U true CN202266301U (en) | 2012-06-06 |
Family
ID=46157099
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN 201120314675 Expired - Lifetime CN202266301U (en) | 2011-08-24 | 2011-08-24 | Turbine machine and turbine engine with same |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202266301U (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104454041A (en) * | 2014-12-19 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Ribbed sealing ring |
| CN104594954A (en) * | 2014-12-15 | 2015-05-06 | 中国南方航空工业(集团)有限公司 | Turbine structure and gas turbine with turbine structure |
| CN106089312A (en) * | 2016-07-29 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of have the turbine disk cavity configuration obturaging and cooling down deflector |
| CN106460539A (en) * | 2014-05-27 | 2017-02-22 | 赛峰飞机发动机公司 | Sealing plate with fuse function |
-
2011
- 2011-08-24 CN CN 201120314675 patent/CN202266301U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106460539A (en) * | 2014-05-27 | 2017-02-22 | 赛峰飞机发动机公司 | Sealing plate with fuse function |
| CN106460539B (en) * | 2014-05-27 | 2018-02-02 | 赛峰飞机发动机公司 | sealing plate with insurance function |
| CN104594954A (en) * | 2014-12-15 | 2015-05-06 | 中国南方航空工业(集团)有限公司 | Turbine structure and gas turbine with turbine structure |
| CN104594954B (en) * | 2014-12-15 | 2016-01-06 | 中国南方航空工业(集团)有限公司 | Turbine structure and there is its gas turbine |
| CN104454041A (en) * | 2014-12-19 | 2015-03-25 | 中国南方航空工业(集团)有限公司 | Ribbed sealing ring |
| CN104454041B (en) * | 2014-12-19 | 2016-08-17 | 中国南方航空工业(集团)有限公司 | Ribbed is obturaged circle |
| CN106089312A (en) * | 2016-07-29 | 2016-11-09 | 中国科学院工程热物理研究所 | A kind of have the turbine disk cavity configuration obturaging and cooling down deflector |
| CN106089312B (en) * | 2016-07-29 | 2017-12-19 | 中国科学院工程热物理研究所 | It is a kind of that there is the turbine disk cavity configuration for obturaging and cooling down deflector |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120606 |