CN202417611U - Turbine blade - Google Patents
Turbine blade Download PDFInfo
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- CN202417611U CN202417611U CN2011205601834U CN201120560183U CN202417611U CN 202417611 U CN202417611 U CN 202417611U CN 2011205601834 U CN2011205601834 U CN 2011205601834U CN 201120560183 U CN201120560183 U CN 201120560183U CN 202417611 U CN202417611 U CN 202417611U
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- turbine blade
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- ribs
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Abstract
The utility model relates to a turbine blade. The turbine blade comprises a blade main body, wherein the blade main body consists of a first end face, a second end face, a leading edge, a trailing edge and a pressure surface part and a suction surface part which extend from the leading edge to the trailing edge; a chamber for communicating the first end face with the second end face through gas is formed in the blade main body; a plurality of spoiling ribs are convexly arranged on the inner wall surface of the chamber; cooling gas enters the chamber from the first end face, is spoiled by the spoiling ribs and flows out of the second end face; and the longitudinal direction of each spoiling rib is basically consistent with the flow direction of the cooling gas. By arranging longitudinal spoiling ribs on the inner wall of the chamber of the turbine blade, heat exchange in the turbine blade can be enhanced, and flow resistance in the turbine blade is reduced, so that the turbine blade can be kept in low temperature level, and the service life of the turbine blade is prolonged.
Description
Technical field
The utility model relates to a kind of turbine blade, relates in particular to a kind of turbine blade with flow-disturbing rib.
Background technique
Along with developing by leaps and bounds of aero engine technology, no matter inlet temperature all significantly improves before aero-engine compressor pressure ratio and the turbine, and this must cause the suffered heat load of turbine blade sharply to increase, and makes it bear very serious thermal stress.
For addressing this problem, except continuous development new material with the new process, one of a crucial factor is that turbine blade is adopted advanced efficient reinforcement cooling technology.The cooling technology of turbine blade mainly carries out from two aspects: be the disturbance of strengthening the inner cooling air of turbine blade on the one hand; Increase the inner heat exchange area of turbine blade; Be to adopt the air film cooling on the other hand, with the convection heat exchange of effective obstruct high-temperature fuel gas to turbine blade at blade surface.
Thereby the inner forced heat exchanging major part of turbine blade in the past is employed in the mode forced heat exchanging that turbine blade inside installs horizontal flow-disturbing rib additional or installs cylindrical turbulence columns additional.Yet; The blade of low-pressure turbine is generally thinner; The inner space is little; Therefore adding traditional flow-disturbing rib can exist following deficiency: flow resistance loss was bigger when one of which, cooling air were flowed through these structures, made turbine blade cooling air under identical inlet pressure be not enough to satisfy the demand to the turbine blade cooling; Two, heat exchange poor effect because bigger flow resistance loss makes cooled gas less, thereby has limited the heat exchange effect.
The model utility content
A purpose of the utility model provides a kind of turbine blade; It has blade body; Blade body partly constitutes by first end face, second end face, leading edge, trailing edge and from pressure side part and suction surface that leading edge extends to trailing edge, and blade body is formed with the chamber that gas is communicated with first end face and second end face within it, on the internal face that forms chamber, convexes with a plurality of flow-disturbing ribs; Wherein, Cooled gas flows out from second end face after first end face enters into chamber and process flow-disturbing rib flow-disturbing, and wherein, each of a plurality of flow-disturbing ribs is arranged to the airflow direction basically identical of its longitudinal direction and cooled gas.
Preferably, a plurality of flow-disturbing ribs are pitched arranged.
More preferably, a plurality of flow-disturbing ribs are arranged on the internal face of pressure side part and on the internal face of suction surface part, wherein, the internal face of pressure side part is arranged with the flow-disturbing rib on the suction surface internal face partly alternately.
Preferably, each of a plurality of flow-disturbing ribs has and comes the U-shaped that flow path direction protrudes out or the part of V-arrangement over against cooled gas.
Preferably, each width of a plurality of flow-disturbing ribs becomes big gradually along the airflow direction of said cooled gas.
Preferably, each of a plurality of flow-disturbing ribs is hollow.
More preferably, each of a plurality of flow-disturbing ribs is three-back-shaped on the cross section that leading edge forms to trailing edge.
Preferably, each height of a plurality of flow-disturbing ribs is 0.2-0.5mm.
Preferably, turbine blade is turborotor or moving turbine blade.
The utility model is through being furnished with flow-disturbing rib longitudinally on the inwall of the chamber of turbine blade; Can strengthen the inner heat exchange of turbine blade; Reduce the inner flow resistance of turbine blade simultaneously, thereby make turbine blade remain on lower temperature levels, improve the working life of turbine blade.
Description of drawings
Fig. 1 is the longitudinal section of the turbine blade of the utility model;
Fig. 2 is the cross-sectional view of the turbine blade of the utility model;
Fig. 3 A shows a kind of flow-disturbing rib of the turbine blade of the utility model, and wherein this flow-disturbing rib has the U-shaped that protrudes out;
Fig. 3 B shows a kind of flow-disturbing rib of the turbine blade of the utility model, and wherein this flow-disturbing rib has the V-arrangement that protrudes out;
Fig. 3 C shows a kind of flow-disturbing rib of the turbine blade of the utility model, and wherein this flow-disturbing rib has along its width of airflow direction of cooled gas and becomes big shape gradually;
Fig. 3 D is a kind of flow-disturbing rib that the turbine blade of the utility model, and wherein this flow-disturbing rib has " returning " font.
Embodiment
In the specific descriptions of following preferred embodiment, will be with reference to constituting the appended accompanying drawing of the utility model.Appended accompanying drawing shows the certain embodiments that can realize the utility model through the mode of example.The embodiment of example is not intended to limit all embodiments according to the utility model.Be appreciated that and under the prerequisite of the scope that does not depart from the utility model, can utilize other embodiments, also can carry out the modification of structural or logicality.Therefore, following specific descriptions are also nonrestrictive, and the scope of the utility model is limited appended claim.
Hereinafter, term " blade body " refers to the airfoil section of blade, its blade vertically on have the profile of basically identical.That is, for turborotor, it does not comprise the upper and lower listrium part integrally formed with airfoil section; For moving turbine blade, it does not comprise that the leaf root part that is connected with turbine shaft also is not included in the integral shroud part on airfoil section top, yet usually, integral shroud part, leaf root part are all integrally formed with airfoil section.
As depicted in figs. 1 and 2, a kind of turborotor is disclosed, it has blade body 100.This blade body 100 constitutes by first end face 102, second end face 104, leading edge 106, trailing edge 108 and from pressure side part 110 and suction surface part 112 that leading edge 106 extends to trailing edge 108.And in blade body 100, be formed with the chamber 114 that gas is communicated with first end face 102 and second end face 104; Has dividing plate 116,118 in the chamber 114; These two dividing plates 116,118 are divided into three sub-chamber with chamber 114, on the internal face of each sub-chamber (in the drawings only at the minimum chamber of circulation area), convex with vertical flow-disturbing rib 120 of a plurality of fork arranged.And, be arranged on the flow-disturbing rib 120 on the internal face of pressure side part 110 and the flow-disturbing rib 120 that is arranged on the internal face of suction surface part 112 relatively and is alternately arranged.The height of flow-disturbing rib is about 0.2-0.5mm, and the specification of looking turbine blade can change to some extent.
Like this, cooled gas flows out from second end face 104 after first end face 102 enters into chamber 114 and process flow-disturbing rib 120 flow-disturbings, and forms airflow direction D, wherein, and the airflow direction D basically identical of the longitudinal direction of flow-disturbing rib 120 and cooled gas.
According to a purpose of the utility model, this longitudinally flow-disturbing rib 120 not only can increase the heat exchange area of the internal face of cooled gas and blade body 100, can also reduce flow resistance with respect to traditional cross rib simultaneously.
Another purpose according to the utility model; Flow-disturbing rib 120 arranges that with fork row mode thereby not only can play the effect that destroys the cooling blast flow boundary layer increases the coefficient of heat transfer; And can also guarantee the circulation area of cooling blast, this is especially suitable for the little low-pressure turbine guide vane of the chamber of blade body.
Purpose further according to the utility model; The interlaced arrangement mode of the flow-disturbing rib 120 of the flow-disturbing rib 120 on the internal face of pressure side part 110 and the internal face of suction surface part 112 can play the effect that guarantees cooled gas circulation area, and this is especially suitable for the little low-pressure turbine guide vane of the chamber of blade body.
In addition, the processing technology of flow-disturbing rib is also fairly simple longitudinally.This rib of flow-disturbing longitudinally is applied on the turbine blade, can reduces the temperature levels of turbine blade effectively, the life-span of turbine blade is improved greatly.
Referring to Fig. 3 A-3D, the various shape of the vertical flow-disturbing rib that is suitable for the utility model purpose has been shown among these figure.Fig. 3 A shows the flow-disturbing rib and has the shape of coming the U-shaped that flow path direction protrudes out over against cooled gas.Fig. 3 B shows the flow-disturbing rib and has the V-arrangement shape of coming flow path direction to protrude out over against cooled gas.Those skilled in the art should be appreciated that the flow-disturbing rib over against cooled gas to come flow path direction to adopt other arcuate shape or adopt other splitter shapes also be feasible.Above-mentioned shape can reduce flow resistance.Fig. 3 C has gone out the flow-disturbing rib to have along its width of airflow direction of cooled gas and become big shape gradually.Fig. 3 D shows the flow-disturbing rib and to the cross section that trailing edge forms, is three-back-shaped in leading edge.That is, for hollow, it helps weight reduction but does not influence the heat exchange effect.
Those skilled in the art should be appreciated that above-mentioned turbine blade promptly can be turborotor and also can be moving turbine blade.
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 innovation and creation that do not exceed in the utility model connotation all fall in the protection domain of the utility model.
Claims (9)
1. turbine blade; It has blade body; Said blade body partly constitutes by first end face, second end face, leading edge, trailing edge and from pressure side part and suction surface that said leading edge extends to said trailing edge; And said blade body is formed with the chamber that gas is communicated with said first end face and said second end face within it; On the internal face that forms said chamber, convex with a plurality of flow-disturbing ribs, wherein, cooled gas flows out from said second end face after said first end face enters into said chamber and the said flow-disturbing rib flow-disturbing of process; It is characterized in that each of said a plurality of flow-disturbing ribs is arranged to the airflow direction basically identical of its longitudinal direction and said cooled gas.
2. turbine blade according to claim 1 is characterized in that, said a plurality of flow-disturbing ribs are pitched arranged.
3. turbine blade according to claim 2; It is characterized in that; Said a plurality of flow-disturbing rib is arranged on the internal face of said pressure side part and on the internal face of said suction surface part; Wherein, the flow-disturbing rib on the internal face of the internal face of said pressure side part and said suction surface part is arranged alternately.
4. turbine blade according to claim 1 is characterized in that, each of said a plurality of flow-disturbing ribs has comes the U-shaped that flow path direction protrudes out or the part of V-arrangement over against cooled gas.
5. turbine blade according to claim 1 is characterized in that, the width of each of said a plurality of flow-disturbing ribs becomes big gradually along the airflow direction of said cooled gas.
6. turbine blade according to claim 1 is characterized in that each of said a plurality of flow-disturbing ribs is hollow.
7. turbine blade according to claim 6, each of said a plurality of flow-disturbing ribs is three-back-shaped in said leading edge to the cross section that said trailing edge forms.
8. according to each described turbine blade of claim 1-7, it is characterized in that the height of each of said a plurality of flow-disturbing ribs is 0.2-0.5mm.
9. according to each described turbine blade of claim 1-7, said turbine blade is turborotor or moving turbine blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205601834U CN202417611U (en) | 2011-12-28 | 2011-12-28 | Turbine blade |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011205601834U CN202417611U (en) | 2011-12-28 | 2011-12-28 | Turbine blade |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202417611U true CN202417611U (en) | 2012-09-05 |
Family
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2011205601834U Expired - Lifetime CN202417611U (en) | 2011-12-28 | 2011-12-28 | Turbine blade |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202417611U (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104533538A (en) * | 2014-12-15 | 2015-04-22 | 厦门大学 | Heat exchange channel wall with rib structure |
| CN108590776A (en) * | 2018-04-24 | 2018-09-28 | 厦门大学 | A kind of turbine blade cooling method using triangular pyramid vortex generator |
| CN109441557A (en) * | 2018-12-27 | 2019-03-08 | 哈尔滨广瀚动力技术发展有限公司 | A kind of high-pressure turbine guide vane of the marine gas turbine with cooling structure |
| CN113374545A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Impingement cooling structure based on array annular raised target plate |
| CN115875084A (en) * | 2023-03-02 | 2023-03-31 | 中国航发四川燃气涡轮研究院 | Laminate cooling structure applied to pressure surface of turbine blade |
-
2011
- 2011-12-28 CN CN2011205601834U patent/CN202417611U/en not_active Expired - Lifetime
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104533538A (en) * | 2014-12-15 | 2015-04-22 | 厦门大学 | Heat exchange channel wall with rib structure |
| CN108590776A (en) * | 2018-04-24 | 2018-09-28 | 厦门大学 | A kind of turbine blade cooling method using triangular pyramid vortex generator |
| CN109441557A (en) * | 2018-12-27 | 2019-03-08 | 哈尔滨广瀚动力技术发展有限公司 | A kind of high-pressure turbine guide vane of the marine gas turbine with cooling structure |
| CN109441557B (en) * | 2018-12-27 | 2024-06-11 | 哈尔滨广瀚动力技术发展有限公司 | High-pressure turbine guide vane of marine gas turbine with cooling structure |
| CN113374545A (en) * | 2021-06-27 | 2021-09-10 | 西北工业大学 | Impingement cooling structure based on array annular raised target plate |
| CN115875084A (en) * | 2023-03-02 | 2023-03-31 | 中国航发四川燃气涡轮研究院 | Laminate cooling structure applied to pressure surface of turbine blade |
| CN115875084B (en) * | 2023-03-02 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Laminate cooling structure applied to turbine blade pressure surface |
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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 | ||
| 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. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20120905 |