CN104594954A - Turbine structure and gas turbine with turbine structure - Google Patents
Turbine structure and gas turbine with turbine structure Download PDFInfo
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- CN104594954A CN104594954A CN201410776799.3A CN201410776799A CN104594954A CN 104594954 A CN104594954 A CN 104594954A CN 201410776799 A CN201410776799 A CN 201410776799A CN 104594954 A CN104594954 A CN 104594954A
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Abstract
The invention provides a turbine structure and a gas turbine with the turbine structure. The turbine structure comprises a turbine disc (10) which is provided with a rotating shaft penetrating through hole (11) and further comprises a flow guide disc (20) which is provided with a rotating shaft avoiding through hole (21), the flow guide disc (20) is fixedly stacked on the turbine disc (10), and a cooling air flow channel is formed between the flow guide disc (20) and the turbine disc (10). According to the turbine structure, the manufacturing cost of a casing is reduced.
Description
Technical field
The present invention relates to technical field of engines, in particular to a kind of turbine structure and the gas turbine with it.
Background technique
At present, the high-pressure turbine dish of gas turbine needs cooled gas to cool it, and the cooling of most high-pressure turbine dish is cooled it by outside gas circuit bleed.In actual production, the existence of outside gas circuit, greatly improves the design difficulty of casing, is easily subject to the overproof impact brought of other structures simultaneously, causes entirety to be scrapped in processing gas circuit process.Existing turbine structure and gas turbine make casing scrappage higher, add manufacture cost.
Summary of the invention
The present invention aims to provide a kind ofly has the turbine structure reducing casing manufacture cost and the gas turbine with it.
To achieve these goals, according to an aspect of the present invention, provide a kind of turbine structure, comprise: the turbine disk, have rotating shaft and wear through hole, turbine structure also comprises: diversion disk, has rotating shaft and dodges through hole, diversion disk stacks and is fixed on the turbine disk, forms cooling air runner between diversion disk and the turbine disk.
Further, cooling air runner comprises the multiple guiding gutters be arranged on diversion disk, and multiple guiding gutter interval in the circumference of diversion disk is arranged, and the bottom land of each guiding gutter is towards the turbine disk.
Further, each guiding gutter extends in the radial direction of diversion disk.
Further, cooling air runner also comprises the annular diversion trench be arranged on the turbine disk, and the bottom land of annular diversion trench is towards diversion disk, and annular diversion trench is connected with multiple guiding gutter respectively.
Further, the outer circumferential face of the turbine disk has blade restraining groove, diversion disk has the blade extended towards the turbine disk and supports annular flange.
Further, the turbine disk has axially the first projection extended towards diversion disk, diversion disk has axially second projection identical with the bearing of trend of axial first projection, axially the second projection is set in axial first projection, cooling air runner also comprises and is formed in rotating shaft and dodges through hole and the gas passage gaps axially between the first projection, and multiple guiding gutter is all connected with gas passage gaps.
Further, axially the outer circumferential face of the second projection has Sealing annular receiving groove.
Further, the aperture that through hole is dodged in rotating shaft is reducing gradually away from the direction of the turbine disk, and axially the outer circumferential face of the first projection shrinks gradually on the direction of diversion disk.
Further, the turbine disk has spaced multiple bolt in the circumferential and wears axially the first through hole, diversion disk has spaced multiple bolt in the circumferential and wears axially the second through hole, adjacent two bolts wear axially has at least one guiding gutter between the second through hole, and multiple bolt wears axially the first through hole and multiple bolt and wears axis the second through hole one_to_one corresponding and arrange and wear bolt.
According to a further aspect in the invention, provide a kind of gas turbine, comprising: blade, have tenon, listrium and blade, gas turbine also comprises: above-mentioned turbine structure, has the radial clearance be connected with cooling air runner between listrium with the turbine disk.
Apply technological scheme of the present invention, be fixed on the turbine disk because diversion disk stacks, cooling air runner is formed between diversion disk and the turbine disk, therefore, cooled gas can flow through cooling air runner and cool the turbine disk, without the need to arranging outside gas circuit, reducing the design difficulty of casing, avoiding casing to scrap.As the above analysis, turbine structure of the present invention reduces the manufacture cost of casing.
Accompanying drawing explanation
The Figure of description forming a application's part is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 shows and looks cross-sectional schematic according to the master of the embodiment of gas turbine of the present invention;
Fig. 2 shows the schematic front view of diversion disk in the embodiment according to turbine structure of the present invention;
Fig. 3 shows the A-A of the diversion disk of Fig. 2 to cross-sectional schematic.
Wherein, the reference character in above-mentioned figure is as follows:
10, wheel disc; 11, rotating shaft wears through hole; 12, annular diversion trench; 13, axial first is protruding; 15, bolt; 20, diversion disk; 21, through hole is dodged in rotating shaft; 22, guiding gutter; 23, blade supports annular flange; 24, axial second is protruding; 25, bolt wears axially the second through hole; 26, gas passage gaps; 27, Sealing annular receiving groove; 30, blade; 31, tenon; 32, listrium; 33, blade; 34, radial clearance; 40, guide shell; 41, water conservancy diversion through hole.
Embodiment
It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.Below with reference to the accompanying drawings and describe the present invention in detail in conjunction with the embodiments.
As depicted in figs. 1 and 2, the turbine structure of the present embodiment comprises the turbine disk 10 and diversion disk 20.The turbine disk 10 has rotating shaft and wears through hole 11.Diversion disk 20 has rotating shaft and dodges through hole 21, and diversion disk 20 stacks and is fixed on the turbine disk 10, forms cooling air runner between diversion disk 20 and the turbine disk 10.
The turbine structure of application the present embodiment, be fixed on the turbine disk 10 because diversion disk 20 stacks, cooling air runner is formed between diversion disk 20 and the turbine disk 10, therefore, cooled gas can flow through cooling air runner and cool the turbine disk 10, without the need to arranging outside gas circuit, reducing the design difficulty of casing, avoiding casing to scrap.As the above analysis, the turbine structure of the present embodiment reduces the manufacture cost of casing.
As shown in Figures 2 and 3, in the present embodiment, cooling air runner comprises the multiple guiding gutters 22 be arranged on diversion disk 20, and multiple guiding gutter 22 interval in the circumference of diversion disk 20 is arranged, and the bottom land of each guiding gutter 22 is towards the turbine disk 10.Adopt said structure, can cooling effect be strengthened.
As shown in Figures 2 and 3, in the present embodiment, each guiding gutter 22 extends in the radial direction of diversion disk 20.Adopt said structure, further enhancing cooling effect.
As depicted in figs. 1 and 2, in the present embodiment, cooling air runner also comprises the annular diversion trench 12 be arranged on the turbine disk 10, and the bottom land of annular diversion trench 12 is towards diversion disk 20, and annular diversion trench 12 is connected with multiple guiding gutter 22 respectively.Adopt said structure, further enhancing cooling effect.
As shown in Figure 1 to Figure 3, in the present embodiment, the outer circumferential face of the turbine disk 10 has blade restraining groove, diversion disk 20 has the blade extended towards the turbine disk 10 and supports annular flange 23.Blade restraining groove is for holding tenon 31, and blade is supported annular flange 23 and supported on listrium 32 to realize the fixing of blade 30.Certainly, as other feasible mode of executions, tenon 31 is directly welded on the turbine disk 10.
As depicted in figs. 1 and 2, in the present embodiment, the turbine disk 10 has axially the first projection 13 extended towards diversion disk 20, diversion disk 20 has axially second projection 24 identical with the bearing of trend of axial first projection 13, axially the second projection 24 is set in axial first projection 13, cooling air runner also comprises and is formed in rotating shaft and dodges through hole 21 and the gas passage gaps 26 axially between the first projection 13, and multiple guiding gutter 22 is all connected with gas passage gaps 26.The join strength with rotating shaft can be improved, by arranging the join strength of axially the second protruding 24 raisings and the turbine disk 10 by arranging axially the first projection 13.By arranging gas passage gaps 26, cooling effect can be strengthened further.
As shown in figures 1 and 3, in the present embodiment, axially the outer circumferential face of the second projection 24 has Sealing annular receiving groove 27.Adopt said structure, axially the second projection 24 and the sealing of guide shell 40 can be improved, avoid cooled gas to overflow.
As shown in figures 1 and 3, in the present embodiment, the aperture that through hole 21 is dodged in rotating shaft reduces gradually on the direction away from the turbine disk 10, and axially the outer circumferential face of the first projection 13 shrinks gradually on the direction of diversion disk 20.Adopt said structure, cooled gas is spread gradually at gas coming through passage gaps 26, and speed reduces, and further enhancing cooling effect.
As shown in figures 1 and 3, in the present embodiment, the turbine disk 10 has spaced multiple bolt in the circumferential and wears axially the first through hole, diversion disk 20 has spaced multiple bolt in the circumferential and wears axially the second through hole 25, adjacent two bolts wear axially has at least one guiding gutter 22 between the second through hole 25, and multiple bolt wears axially the first through hole and multiple bolt and wears axis the second through hole 25 one_to_one corresponding and arrange and wear bolt 15.Adopt said structure, be convenient to dismounting diversion disk 20.
Present invention also provides a kind of gas turbine, as shown in Figure 1, the gas turbine of the present embodiment comprises the turbine structure of blade 30, guide shell 40 and above-described embodiment.Blade 30 has tenon 31, listrium 32 and blade 33.There is between listrium 32 with the turbine disk 10 radial clearance 34 be connected with cooling air runner.Cryogenic high pressure air part after centrifugal high pressure impeller enters inner chamber by the water conservancy diversion through hole 41 on guide shell 40 outer circumferential face, guiding gutter 22 on the gap and diversion disk 20 of diversion disk 20 and the turbine disk 10 arrives the annular diversion trench 12 of the turbine disk 10, the turbine disk 10 is cooled, from tenon tooth gap, flows into blast tube afterwards.Guide shell 40 is fixed by bolt 15 and is located on diversion disk 20.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (10)
1. a turbine structure, comprising:
The turbine disk (10), have rotating shaft and wear through hole (11), it is characterized in that, described turbine structure also comprises:
Diversion disk (20), there is rotating shaft and dodge through hole (21), described diversion disk (20) stacks and is fixed on the described turbine disk (10), forms cooling air runner between described diversion disk (20) and the described turbine disk (10).
2. turbine structure according to claim 1, it is characterized in that, described cooling air runner comprises the multiple guiding gutters (22) be arranged on described diversion disk (20), described multiple guiding gutter (22) interval in the circumference of described diversion disk (20) is arranged, and the bottom land of each described guiding gutter (22) is towards the described turbine disk (10).
3. turbine structure according to claim 2, is characterized in that, each described guiding gutter (22) extends in the radial direction of described diversion disk (20).
4. turbine structure according to claim 2, it is characterized in that, described cooling air runner also comprises the annular diversion trench (12) be arranged on the turbine disk (10), the bottom land of described annular diversion trench (12) is towards described diversion disk (20), and described annular diversion trench (12) is connected with described multiple guiding gutter (22) respectively.
5. turbine structure according to claim 1, it is characterized in that, the outer circumferential face of the described turbine disk (10) has blade restraining groove, and described diversion disk (20) has the blade extended towards the described turbine disk (10) and supports annular flange (23).
6. turbine structure according to claim 2, it is characterized in that, the described turbine disk (10) has axially the first projection (13) extended towards described diversion disk (20), described diversion disk (20) has axially second projection (24) identical with the bearing of trend of described axis first projection (13), described axis second projection (24) is set on described axis first projection (13), described cooling air runner also comprises and is formed in described rotating shaft and dodges gas passage gaps (26) between through hole (21) and described axis first projection (13), described multiple guiding gutter (22) is all connected with described gas passage gaps (26).
7. turbine structure according to claim 6, is characterized in that, the outer circumferential face of described axis second projection (24) has Sealing annular receiving groove (27).
8. turbine structure according to claim 6, it is characterized in that, the aperture that through hole (21) is dodged in described rotating shaft reduces gradually on the direction away from the described turbine disk (10), and the outer circumferential face of described axis first projection (13) shrinks gradually on the direction of described diversion disk (20).
9. turbine structure according to claim 2, it is characterized in that, the described turbine disk (10) has spaced multiple bolt in the circumferential and wears axially the first through hole, described diversion disk (20) has spaced multiple bolt in the circumferential and wears axially the second through hole (25), adjacent two bolts wear axially has guiding gutter described at least one (22) between the second through hole (25), described multiple bolt wears axially the first through hole and described multiple bolt and wears axis the second through hole (25) one_to_one corresponding and arrange and wear bolt (15).
10. a gas turbine, comprising:
Blade (30), have tenon (31), listrium (32) and blade (33), it is characterized in that, described gas turbine also comprises:
Turbine structure according to any one of claim 1 to 9, has the radial clearance (34) be connected with described cooling air runner between described listrium (32) with the described turbine disk (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410776799.3A CN104594954B (en) | 2014-12-15 | 2014-12-15 | Turbine structure and there is its gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410776799.3A CN104594954B (en) | 2014-12-15 | 2014-12-15 | Turbine structure and there is its gas turbine |
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| Publication Number | Publication Date |
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| CN104594954A true CN104594954A (en) | 2015-05-06 |
| CN104594954B CN104594954B (en) | 2016-01-06 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201410776799.3A Active CN104594954B (en) | 2014-12-15 | 2014-12-15 | Turbine structure and there is its gas turbine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104895622A (en) * | 2015-06-24 | 2015-09-09 | 中国航空动力机械研究所 | Gas turbine guide flow disk |
| CN111390113A (en) * | 2020-04-17 | 2020-07-10 | 中国航发北京航空材料研究院 | Method for accurately controlling outline dimension of hollow single crystal turbine working blade |
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| US20120082568A1 (en) * | 2010-10-04 | 2012-04-05 | Rolls-Royce Plc | Turbine disc cooling arrangement |
| CN202266301U (en) * | 2011-08-24 | 2012-06-06 | 中国航空动力机械研究所 | Turbine machine and turbine engine with same |
| CN202578804U (en) * | 2012-04-13 | 2012-12-05 | 中国航空动力机械研究所 | Densification device for turbine rabbet |
| CN103061830A (en) * | 2013-01-17 | 2013-04-24 | 中国科学院工程热物理研究所 | Worm gear damping method and worm gear damping structure |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| SU850871A1 (en) * | 1979-10-29 | 1981-07-30 | Всесоюзный Дважды Ордена Трудовогокрасного Знамени Теплотехническийнаучно-Исследовательский Институтим.Ф.Э.Дзержинского | Turbomachine rotor |
| SU1126025A1 (en) * | 1982-06-01 | 1996-04-10 | Производственное объединение "Турбомоторный завод" | Cooled working wheel of gas turbine |
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2014
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Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101178029A (en) * | 2006-11-10 | 2008-05-14 | 通用电气公司 | Interstage cooled turbine engine |
| US20120082568A1 (en) * | 2010-10-04 | 2012-04-05 | Rolls-Royce Plc | Turbine disc cooling arrangement |
| CN202266301U (en) * | 2011-08-24 | 2012-06-06 | 中国航空动力机械研究所 | Turbine machine and turbine engine with same |
| CN202578804U (en) * | 2012-04-13 | 2012-12-05 | 中国航空动力机械研究所 | Densification device for turbine rabbet |
| CN103061830A (en) * | 2013-01-17 | 2013-04-24 | 中国科学院工程热物理研究所 | Worm gear damping method and worm gear damping structure |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104895622A (en) * | 2015-06-24 | 2015-09-09 | 中国航空动力机械研究所 | Gas turbine guide flow disk |
| CN104895622B (en) * | 2015-06-24 | 2016-08-24 | 中国航空动力机械研究所 | A kind of gas turbine flow guiding disc |
| CN111390113A (en) * | 2020-04-17 | 2020-07-10 | 中国航发北京航空材料研究院 | Method for accurately controlling outline dimension of hollow single crystal turbine working blade |
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| Publication number | Publication date |
|---|---|
| CN104594954B (en) | 2016-01-06 |
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Address after: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee after: China Hangfa South Industrial Co. Ltd. Address before: 412002 Dong Jiaduan, Zhuzhou, Hunan Patentee before: China Southern Airlines Industry (Group) Co., Ltd. |
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