CN202417612U - Turbine guide blade - Google Patents
Turbine guide blade Download PDFInfo
- Publication number
- CN202417612U CN202417612U CN2011205540563U CN201120554056U CN202417612U CN 202417612 U CN202417612 U CN 202417612U CN 2011205540563 U CN2011205540563 U CN 2011205540563U CN 201120554056 U CN201120554056 U CN 201120554056U CN 202417612 U CN202417612 U CN 202417612U
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- China
- Prior art keywords
- impact
- housing
- turborotor
- turbulence columns
- shell
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- 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.)
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Abstract
The utility model provides a turbine guide blade, comprising a shell and a plurality of gas film holes, wherein the shell is provided with a front edge, a back edge, a pressure face and an attraction face; the pressure face and the attraction face extend from the front edge to the back edge; a cavity and an air inlet communicated with the cavity are formed in the shell; and the air film holes are formed in the shell and are communicated with the cavity. An impact tube and a plurality of turbulent flow columns are contained in the cavity, wherein the impact tube is communicated with the air inlet, and is provided with a plurality of impact holes; at least one part of the outer surface of the impact tube is separated from the inner wall of the shell so as to form an impact channel; and the turbulent flow columns are configured in the impact channel, so that cooling air enters the impact tube through the air inlet and is discharged from the air film holes by sequentially flowing through the impact hole and the impact channel. The turbulent flow columns are arranged to enhance the disturbance of the cooling air and the inner wall of the shell, so that the heat exchange effect of the inner wall of the shell in an impact stagnation point area is enhanced. Meanwhile, the cooling air is directly subjected to heat convection with the turbulent flow columns. Heat on the wall face is directly taken away by the cooling air through the turbulent flow columns.
Description
Technical field
The utility model relates to a kind of turborotor.
Background technique
In a lot of fields, gas turbine is used to drive generator or work mechanism.At this, utilize the energy of fuel to make turbine shaft rotate.For this reason, fuel burns in a firing chamber, is also imported wherein by the air after the gas compressor compression.In the firing chamber, form the working medium of HTHP, again through the acting of expanding of a turbine unit that is connected the back, firing chamber through fuel combustion.
In order to make turbine shaft produce high speed rotary motion, on turbine shaft, be provided with many working blades, they drive turbine shaft through the energy from the working medium of firing chamber.In order in turbine unit, working medium to be carried out the fluid transmission; The turborotor that is connected with turbine shroud (or claiming turbine casing) also is set between adjacent working blade usually; Like this, a turborotor and an adjacent moving turbine blade are commonly called a turbine stage.
At this, turborotor is fixed on the guide vane support of turbine unit through listrium.Because working medium is a HTHP, be under the high heat load constantly by the assembly of this working medium and part.Therefore, work safely and reliably, need cool off efficiently turborotor in order to guarantee turbo machine.
Fig. 1 shows conventional turborotor 10; Its housing 12 is provided with air film hole 14; Has the conduit 16 of impact in the chamber that housing 12 forms; Impact on the conduit 16 being furnished with impact opening 18, thereby cooled gas enters into from the inlet hole of guide vane 10 and impacts conduit 16 and discharge the cooling of accomplishing turborotor 10 via impact opening 18 and air film hole 14.Though the turborotor of this structure is easy to manufacturing; Yet impacting cooling effect is local strengthening, undesirable at the position cooling effect of not arranging impact opening; And the assignment of traffic of effluenting from air film hole 14 after gas shock is intact is also wayward.
The model utility content
In order to solve the unfavorable technical problem of cooling effect, the utility model provides a kind of turborotor.This turborotor comprises: housing, shock tube and a plurality of turbulence columns.This housing has leading edge, trailing edge and extends to the pressure side and the suction surface of trailing edge from leading edge, and the suction port that in housing, is formed with chamber and is communicated with chamber, a plurality of air film holes are formed on the housing and are communicated to chamber.Shock tube and a plurality of turbulence columns are contained in the chamber, and wherein, shock tube is communicated with suction port, has a plurality of impact openings on it, and the inwall of its at least a portion outer surface and housing is spaced apart to form the impact passage; These a plurality of turbulence columns are configured in impacts in the passage.Like this, cooled gas enter in the shock tube via suction port and flow through successively impact opening with impact passage and discharge from air film hole again.
Preferably, a plurality of turbulence columns and housing are integrally formed.This realizes than being easier to such as cast form for processing technology.
Preferably, housing is that monocrystal material is processed, and shock tube is that high-temperature alloy material is processed.
Preferably, a plurality of turbulence columns are layouts interlaced with each other.Like this, can strengthen the flow-disturbing effect.
Preferably, the diameter of at least two turbulence columns in a plurality of turbulence columns is different.
Preferably, the distribution density of a plurality of turbulence columns in impacting passage is minimum at the leading edge place near housing.
Turborotor than routine; New blade structure disclosed in the utility model is owing to be provided with turbulence columns; Strengthened the disturbance of the inwall of cooled gas and housing, do not made to strengthen, simultaneously in the inwall heat exchange effect of impacting the regional housing in stationary point; Cooled gas directly with the turbulence columns convection heat exchange, the heat on the wall passes through the turbulence columns gas that directly is cooled and takes away.
In addition; Can control the assignment of traffic situation that cooled gas in the passage flows out from the air film hole of housing of impacting through regulating the distribution density of turbulence columns in impacting passage; As above preferred embodiment said; The distribution density of a plurality of turbulence columns in impacting passage is arranged to the minimum cooling gas flow maximum that can make edge outflow in the past so that cooling effect is the strongest at the leading edge place near housing, this is because the leading edge of turborotor is the worst position of environment that suffers.As above preferred embodiment said, the distribution density of turbulence columns also can realize through the diameter that changes turbulence columns.
Description of drawings
Fig. 1 is the schematic representation of the turborotor 10 of routine;
Fig. 2 is a kind of schematic representation preferred embodiment of the turborotor 100 of the utility model.
Embodiment
As shown in Figure 2, a kind of turborotor 100 is disclosed, it includes housing 102, shock tube 104 and turbulence columns 106.Wherein, this housing 102 can be formed by monocrystal material, pressure side and suction surface that it has leading edge, trailing edge and extends to trailing edge from leading edge.The suction port (not shown) that in housing 102, is formed with chamber 108 and is communicated with chamber 108.Be formed with a plurality of air film holes 110 on the housing 102 and this a plurality of air film holes 110 are connected with above-mentioned chamber 108.Accommodate the shock tube 104 that is communicated with suction port in the chamber 108, this shock tube 104 can be formed by high-temperature alloy material, has a plurality of impact openings 112 on it, and the inwall of the outer surface of shock tube 104 and housing 102 is spaced apart to form impact passage 114.Above-mentioned a plurality of turbulence columns 106 is configured in impacts in the passage 114, and wherein, thereby the arrangement of turbulence columns is the flow-disturbing better effects if of layout interlaced with each other to cooling blast more excellently.
Like this, in when operation, cooling air know from experience suction port via housing 102 enter in the shock tube 104 and flow through successively impact openings 112 with impact passage 114 and discharge from air film hole 110 again.Wherein, This cooled gas can impact in impacting passage 114 and change its original path of travel on the turbulence columns 106; This not only can make the cooled gas and the heat exchange of the internal face of heat increase; And can make cooled gas arrive those on the internal face that impacts the zone, stationary point, final, most of heat of housing 102 gas that can directly be cooled is taken away.
Those skilled in the art should be appreciated that a part of outer surface of this shock tube 104 contacts with the internal face of housing 102 and passage 114 is impacted in the outer surface of other parts of shock tube 104 and the spaced apart formation of internal face of housing 102, also can realize.
Can control and impact in the passage 114 cooled gas through regulating the distribution density of turbulence columns 106 in impacting passage 114 from the assignment of traffic situation of air film hole 110 outflows of housing 102.The utility model preferred embodiment in, can make cooling gas flow maximum that edge in the past flows out so that the air film cooling effect is the strongest thereby the distribution density of turbulence columns 106 in impacting passage 114 is arranged to minimum at the leading edge place near housing 102.The leading edge of turborotor 100 is to suffer the worst position of environment to need a large amount of air film holes 110 to carry out air film to cool off so this is; Above-mentioned design (promptly; The distribution density of turbulence columns 106 near the leading edge place for minimum) can avoid the position of opening of the air film hole 110 on the housing 102 on the one hand; Promptly; Processing to air film hole 110 does not exert an influence, thus on the other hand turbulence columns 106 then can strengthen other regional heat exchange effects has remedied the unconspicuous deficiency of other regional air film cooling effects more greatly in other regional distribution densities.In addition, the distribution density of turbulence columns 106 can also realize with row's number through the diameter that changes turbulence columns 106.For example, the diameter of at least two turbulence columns 106 is designed to different, arranges that with this distribution density of turbulence columns 106 also is feasible.
For the convenience of making, the utility model can adopt for example ceramic core casting technique, and like this, the housing 102 of turborotor 100 and turbulence columns 106 just can be by integrally formed.Because chamber 108 is straight passage, thus at this if adopt the ceramic core casting technique, then depoling technology can relatively easily realize.
Though foregoing description is to the utility model detailed explanation of contrasting; But these are just illustrative to the utility model; Rather than to the restriction of the utility model, any model utility that does not exceed in the utility model connotation is created, and all falls in the protection domain of the utility model.
Claims (9)
1. turborotor comprises:
Housing, it has leading edge, trailing edge and extends to the pressure side and the suction surface of said trailing edge, the suction port that in said housing, is formed with chamber and is communicated with chamber from said leading edge;
A plurality of air film holes, it is formed on the said housing and is communicated to said chamber;
It is characterized in that, accommodate in the said chamber:
Shock tube is communicated with said suction port, has a plurality of impact openings on it, and the inwall of its at least a portion outer surface and said housing is spaced apart to form the impact passage;
A plurality of turbulence columns, it is configured in the said impact passage;
By this, cooled gas enters into also flow through successively in the said shock tube said impact opening and said impact passage again from said air film hole discharge via said suction port.
2. turborotor according to claim 1 is characterized in that, said a plurality of turbulence columns and said housing are integrally formed.
3. turborotor according to claim 1 and 2 is characterized in that, said housing is that monocrystal material is processed, and said shock tube is that high-temperature alloy material is processed.
4. turborotor according to claim 1 and 2 is characterized in that, said a plurality of turbulence columns are layouts interlaced with each other.
5. turborotor according to claim 1 and 2 is characterized in that, the diameter of at least two turbulence columns in said a plurality of turbulence columns is different.
6. turborotor according to claim 4 is characterized in that, the diameter of at least two turbulence columns in said a plurality of turbulence columns is different.
7. turborotor according to claim 1 and 2 is characterized in that, the distribution density of said a plurality of turbulence columns in said impact passage is minimum at the said leading edge place near said housing.
8. turborotor according to claim 4 is characterized in that, the distribution density of said a plurality of turbulence columns in said impact passage is minimum at the said leading edge place near said housing.
9. turborotor according to claim 5 is characterized in that, the distribution density of said a plurality of turbulence columns in said impact passage is minimum at the said leading edge place near said housing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205540563U CN202417612U (en) | 2011-12-27 | 2011-12-27 | Turbine guide blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205540563U CN202417612U (en) | 2011-12-27 | 2011-12-27 | Turbine guide blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202417612U true CN202417612U (en) | 2012-09-05 |
Family
ID=46742385
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205540563U Expired - Lifetime CN202417612U (en) | 2011-12-27 | 2011-12-27 | Turbine guide blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202417612U (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103306744A (en) * | 2013-07-03 | 2013-09-18 | 中国航空动力机械研究所 | Cooling device for guide vane |
| CN103775136A (en) * | 2012-10-23 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Vane |
| CN103806953A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Novel air film holes with inclination angles |
| CN108331617A (en) * | 2017-01-03 | 2018-07-27 | 通用电气公司 | For impinging cooling component and include the rotating machinery of the component |
| CN110821573A (en) * | 2019-12-03 | 2020-02-21 | 沈阳航空航天大学 | Turbine blade for slowing down cooling effect degradation by regulating and controlling internal dust deposition position |
| CN113513372A (en) * | 2021-07-28 | 2021-10-19 | 中国航发湖南动力机械研究所 | Double-wall turbine guide blade with small air guiding amount |
| CN113623011A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
-
2011
- 2011-12-27 CN CN2011205540563U patent/CN202417612U/en not_active Expired - Lifetime
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103775136A (en) * | 2012-10-23 | 2014-05-07 | 中航商用航空发动机有限责任公司 | Vane |
| CN103775136B (en) * | 2012-10-23 | 2015-06-10 | 中航商用航空发动机有限责任公司 | Vane |
| CN103306744A (en) * | 2013-07-03 | 2013-09-18 | 中国航空动力机械研究所 | Cooling device for guide vane |
| CN103806953A (en) * | 2014-01-20 | 2014-05-21 | 北京航空航天大学 | Novel air film holes with inclination angles |
| CN108331617A (en) * | 2017-01-03 | 2018-07-27 | 通用电气公司 | For impinging cooling component and include the rotating machinery of the component |
| CN110821573A (en) * | 2019-12-03 | 2020-02-21 | 沈阳航空航天大学 | Turbine blade for slowing down cooling effect degradation by regulating and controlling internal dust deposition position |
| CN113623011A (en) * | 2021-07-13 | 2021-11-09 | 哈尔滨工业大学 | Turbine blade |
| CN113513372A (en) * | 2021-07-28 | 2021-10-19 | 中国航发湖南动力机械研究所 | Double-wall turbine guide blade with small air guiding amount |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CP03 | Change of name, title or address |
Address after: 200241 Minhang District Lianhua Road, Shanghai, No. 3998 Patentee after: China Hangfa commercial aviation engine limited liability company Address before: 201109 Shanghai city Minhang District Hongmei Road No. 5696 Room 101 Patentee before: AVIC Commercial Aircraft Engine Co.,Ltd. |
|
| CP03 | Change of name, title or address | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120905 |
|
| CX01 | Expiry of patent term |