CN204663595U - Gas turbine turbine gas flow regulation structure - Google Patents
Gas turbine turbine gas flow regulation structure Download PDFInfo
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- CN204663595U CN204663595U CN201520191234.9U CN201520191234U CN204663595U CN 204663595 U CN204663595 U CN 204663595U CN 201520191234 U CN201520191234 U CN 201520191234U CN 204663595 U CN204663595 U CN 204663595U
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- turbine
- mounting groove
- vertical portion
- horizontal part
- stator assembly
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Abstract
The utility model relates to gas turbine structure design field, provides a kind of gas turbine turbine gas flow regulation structure, for regulating the Throughput between the turbine rotor subassembly of annular and turbine stator assembly.This structure comprises adjustment sheet; The external circumferential of turbine rotor subassembly offers the first mounting groove, and an axial side of turbine stator assembly offers the second mounting groove; Adjustment sheet comprises horizontal part and vertical portion, a side margin of horizontal part and the side edge conjunction of vertical portion, and Relative vertical, and the opposite side edge movable of horizontal part is inserted in the second mounting groove; The opposite side edge of vertical portion is provided with several vents, and activity is inserted in the first mounting groove.When there is the changing of the relative positions due to the skewness of air pressure between turbine stator assembly and turbine rotor subassembly, vent on vertical portion exposes from the first mounting groove, thus make high-pressure area release pressure, and then realize regulating the axial relative equilibrium between turbine stator assembly and turbine rotor subassembly.
Description
Technical field
The utility model relates to gas turbine structure design field, provides a kind of gas turbine turbine gas flow regulation structure especially.
Background technique
During gas turbine work, Turbine section contacts with high-temperature fuel gas, need introduce cooled gas cool turbine stator part and turbine rotor parts from other positions.Turbine stator part and turbine rotor parts upwards form front cooled gas chamber and rear cooled gas chamber at turbine spindle, cooled gas in front cooled gas chamber is along turbine spindle to flowing into rear cooled gas chamber backward, needed for the cooled gas chamber of front and back, pressure of compressed air is different, need arrange gas flow control structure in turbine stator part lower end.When normally working, along with the rising of turbine stator part and turbine rotor parts own temperature, turbine stator part and turbine rotor parts extend to expanded by heating in radial direction at turbine spindle, due to the two reason such as material, structure, turbine stator part is different from the elongation of turbine rotor parts, this just require gas flow control structure herein can turbine spindle to radial direction on carry out self-adaptative adjustment.
Traditional industry gas turbine is welded with height honeycomb at turbine lower, as shown in Figure 1, honeycomb 6 is welded with in the lower end of turbine stator assembly 1, turbine rotor subassembly 2 is processed with turbine rotor stage teeth 7, honeycomb 6 processes the different honeycomb of the height corresponding from turbine rotor stage teeth 76, rely on turbine rotor stage teeth 7 and honeycomb 6 to form cooled gas runner passage, control cooled gas flow herein.When combustion engine startup, stopping or working state change greatly, turbine stator assembly is different with the thermal response of turbine rotor subassembly, stage teeth and honeycomb turbine spindle to radial direction on often produce scratching phenomenon, after honeycomb is worn away, the gap width of its design point can not ensure, cause gas flow to strengthen, stage teeth and honeycomb scratching simultaneously can shorten its structural life-time.Because stage teeth is directly processed on turbine rotor, its processing request is higher, cannot change when it loses efficacy, and brings the flow of gas can not meet cooling requirement, causes the reduction of component life shortening and combustion engine efficiency; Unit operation safety is threatened time serious.
Model utility content
(1) technical problem that will solve
The purpose of this utility model is to provide one can solve the problems such as the scraped finish of industry gas turbine turbine stator partial cell, turbine rotor part stage teeth processing request high and life-span can not ensure preferably, can improve gas turbine Turbine section functional reliability, stability and the gas turbine turbine gas flow regulation structure in life-span simultaneously.
(2) technological scheme
For achieving the above object, the utility model provides a kind of gas turbine turbine gas flow regulation structure, for regulating the Throughput between the turbine rotor subassembly of annular and turbine stator assembly, comprises adjustment sheet;
The external circumferential of described turbine rotor subassembly offers the first mounting groove, and an axial side of described turbine stator assembly offers the second mounting groove;
Described adjustment sheet comprises horizontal part and vertical portion, a side margin of described horizontal part and the side edge conjunction of described vertical portion, and described horizontal part and vertical portion Relative vertical, and the opposite side edge movable of described horizontal part is inserted in described second mounting groove; The opposite side edge of described vertical portion is provided with several vents, and activity is inserted in described first mounting groove.
Preferably, the side margin that described horizontal part is plugged in described second mounting groove has wave structure, and the wave of described wave structure extends along the axis of described turbine stator assembly.
Preferably, the opening of described second mounting groove is provided with the limited part extended internally, and described limited part is used for being formed spacing to described wave structure in the axial direction.
Preferably, described adjustment sheet also comprises joint, and the cross section of described joint takes the shape of the letter U, and described horizontal part is connected with the both sides of the edge of vertical portion by described joint.
(3) beneficial effect
A kind of gas turbine turbine gas flow regulation structure that the utility model provides, for regulating the Throughput between the turbine rotor subassembly of annular and turbine stator assembly, comprises adjustment sheet; The external circumferential of turbine rotor subassembly offers the first mounting groove, and an axial side of turbine stator assembly offers the second mounting groove; Adjustment sheet comprises horizontal part and vertical portion, a side margin of horizontal part and the side edge conjunction of vertical portion, and horizontal part and vertical portion Relative vertical, and the opposite side edge movable of horizontal part is inserted in the second mounting groove; The opposite side edge of vertical portion is provided with several vents, and activity is inserted in the first mounting groove.When there is the changing of the relative positions due to the skewness of air pressure between turbine stator assembly and turbine rotor subassembly, vent on vertical portion is adaptive to be exposed from the first mounting groove, thus make high-pressure area release pressure, and then realize regulating the axial relative equilibrium between turbine stator assembly and turbine rotor subassembly.
Accompanying drawing explanation
Fig. 1 is the schematic diagram of the gas turbine turbine gas flow regulation structure of prior art;
Fig. 2 is the schematic diagram of a kind of gas turbine turbine gas flow regulation structure of the utility model embodiment;
Fig. 3 is the schematic diagram of the adjustment sheet of the utility model embodiment.
Reference character:
1, turbine stator assembly; 11, the second mounting groove; 2, turbine rotor subassembly; 21, the first mounting groove; 3, adjustment sheet; 31, horizontal part; 32, vertical portion; 33, vent; 4, front cooled gas chamber; 5, rear cooled gas chamber; 6, honeycomb; 7, turbine rotor stage teeth.
Embodiment
Below in conjunction with drawings and Examples, embodiment of the present utility model is described in further detail.Following examples for illustration of the utility model, but are not used for limiting scope of the present utility model.
In description of the present utility model, except as otherwise noted, term " on ", D score, " top ", " bottom ", the orientation of the instruction such as " longitudinal direction " or state relation be based on orientation shown in the drawings or state relation, only the utility model and simplified characterization for convenience of description, instead of the mechanism of instruction or hint indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.
In description of the present utility model, it should be noted that, unless otherwise clearly defined and limited, term " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be directly be connected, also indirectly can be connected by intermediary.For the ordinary skill in the art, concrete condition the concrete meaning of above-mentioned term in the utility model can be understood.
As shown in Figure 2, a kind of gas turbine turbine gas flow regulation structure that the utility model provides, for regulating the Throughput between the turbine rotor subassembly 2 of annular and turbine stator assembly 1, this regulation structure comprises adjustment sheet 3; The external circumferential of described turbine rotor subassembly 2 offers the first mounting groove 21, and an axial side of described turbine stator assembly 1 offers the second mounting groove 11.Again shown in composition graphs 3, described adjustment sheet 3 comprises horizontal part 31 and vertical portion 32, one side margin of described horizontal part 31 and the side edge conjunction of described vertical portion 32, and described horizontal part 31 and vertical portion 32 Relative vertical, the opposite side edge movable of described horizontal part 31 is inserted in described second mounting groove 11; The opposite side edge of described vertical portion 32 is provided with several vents 33, and activity is inserted in described first mounting groove 21.
With sprue fuel gas flow direction for turbine spindle to, through the obstruct of adjustment sheet 3, annular gap between turbine stator assembly 1 and turbine rotor subassembly 2 is separated into front cooled gas chamber 4 and rear cooled gas chamber 5, cooled gas the past, cooled gas chamber 4 was along turbine spindle to being leaked into rear cooled gas chamber 5 backward, usually after, the comparatively front cold fluid chamber of degassing of cooled gas chamber 5 has pressure drop, cooling air can be accumulated and form high pressure in front cooled gas chamber 4, usually there is the phenomenon that air flow method is uneven in the circumferential in the cold body that degass in front cooled gas chamber 4, high-pressure area is formed thus in a certain radial side, by the impact of this high-pressure area, axial dipole field can be there is between turbine rotor subassembly 2 and turbine stationary vane assembly, namely the gap between the turbine rotor subassembly 2 at this high-pressure area place and turbine stator assembly 1 can increase, if this gap is excessive, the stable operation of gas turbine can be affected, and because the present embodiment by arranging some vents 33 on the vertical portion 32 of adjustment sheet 3, when turbine rotor subassembly 2 increases in the gap of a certain radial side with turbine stator assembly 1, the motion of outwards extracting is done from the first mounting groove 21 in the vertical portion 32 being arranged in this radial side, vent 33 on the vertical portion 32 of this side also more exposes thereupon, thus increase the ventilation capacity of this radial side, the air pressure of this radial side just can reduce thereupon, turbine rotor subassembly 2 and turbine stator assembly 1 just can reduce in the gap of this side thereupon, the object in gap between stable turbine rotor subassembly 2 and turbine stator assembly 1 is adjusted to thus by Throughput.
Wherein, the side margin that described horizontal part 31 is plugged in described second mounting groove 11 preferably has wave structure, the wave of described wave structure extends vertically, when there is the larger axial changing of the relative positions with turbine stator assembly 1 in turbine rotor subassembly 2, in the process, the end of horizontal part 31 may touch the bottom of the second mounting groove 11, if now the changing of the relative positions in this direction continues to increase, the horizontal part 31 with wave structure just can adaptively compress, and avoids horizontal part 31 produce excessive stresses and damage thus.
Further, also can arrange at the opening of described second mounting groove 11 limited part extended internally, described limited part is used for being formed spacing to described wave structure in the axial direction, deviates from from the second chute for preventing wave structure.
Further, the gas turbine turbine gas flow regulation structure of the present embodiment also comprises joint, and the cross section of described joint takes the shape of the letter U, and described horizontal part 31 is connected with the both sides of the edge of vertical portion 32 by described joint.The axial changing of the relative positions is there is between turbine stationary vane assembly and turbine rotor subassembly 2, and wave structure is when touching the limited part of the second mounting groove 11 opening, if now the changing of the relative positions in this direction continues to increase, the elasticity of the U-shaped structure adaptability of joint is launched, make vertical portion 32 that excessive deflection not occur, ensure that and between vertical portion 32 and the first mounting groove 21, to plug move stable; In addition, when turbine rotor subassembly 2 and the gap smaller of a certain radial side of turbine stator assembly 1, and the bottom of vertical portion 32 is when touching the bottom of the first mounting groove 21, if now turbine rotor subassembly 2 and turbine stator assembly 1 continue to reduce in the gap of this radial side, the elasticity adduction of the U-shaped structure adaptability of joint, avoid vertical portion 32 produce excessive stresses and damage, also can reduce the frictional force between the end of vertical portion 32 and the bottom of the first mounting groove 21 simultaneously.
The above is only preferred implementation of the present utility model; should be understood that; for those skilled in the art; under the prerequisite not departing from the utility model know-why; can also make some improvement and replacement, these improve and replace and also should be considered as protection domain of the present utility model.
Claims (4)
1. a gas turbine turbine gas flow regulation structure, for regulating the Throughput between the turbine rotor subassembly (2) of annular and turbine stator assembly (1), is characterized in that, comprise adjustment sheet (3);
The external circumferential of described turbine rotor subassembly (2) offers the first mounting groove (21), and an axial side of described turbine stator assembly (1) offers the second mounting groove (11);
Described adjustment sheet (3) comprises horizontal part (31) and vertical portion (32), one side margin of described horizontal part (31) and the side edge conjunction of described vertical portion (32), and described horizontal part (31) and vertical portion (32) Relative vertical, the opposite side edge movable of described horizontal part (31) is inserted in described second mounting groove (11); The opposite side edge of described vertical portion (32) is provided with several vents (33), and activity is inserted in described first mounting groove (21).
2. a kind of gas turbine turbine gas flow regulation structure according to claim 1, it is characterized in that, the side margin that described horizontal part (31) is plugged in described second mounting groove (11) has wave structure, and the wave of described wave structure extends along the axis of described turbine stator assembly (1).
3. a kind of gas turbine turbine gas flow regulation structure according to claim 2, it is characterized in that, the opening of described second mounting groove (11) is provided with the limited part extended internally, and described limited part is used for being formed spacing to described wave structure in the axial direction.
4. a kind of gas turbine turbine gas flow regulation structure according to claim 1, it is characterized in that, described adjustment sheet (3) also comprises joint, the cross section of described joint takes the shape of the letter U, and described horizontal part (31) is connected by the both sides of the edge of described joint with vertical portion (32).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520191234.9U CN204663595U (en) | 2015-03-31 | 2015-03-31 | Gas turbine turbine gas flow regulation structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520191234.9U CN204663595U (en) | 2015-03-31 | 2015-03-31 | Gas turbine turbine gas flow regulation structure |
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| Publication Number | Publication Date |
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| CN204663595U true CN204663595U (en) | 2015-09-23 |
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| CN201520191234.9U Active CN204663595U (en) | 2015-03-31 | 2015-03-31 | Gas turbine turbine gas flow regulation structure |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113187610A (en) * | 2021-06-15 | 2021-07-30 | 浙江燃创透平机械股份有限公司 | Gas turbine gas flow adjusting structure |
| CN113738453A (en) * | 2021-11-08 | 2021-12-03 | 中国航发四川燃气涡轮研究院 | Turbine guide vane cooling air flow adjusting device |
-
2015
- 2015-03-31 CN CN201520191234.9U patent/CN204663595U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN113187610A (en) * | 2021-06-15 | 2021-07-30 | 浙江燃创透平机械股份有限公司 | Gas turbine gas flow adjusting structure |
| CN113187610B (en) * | 2021-06-15 | 2022-04-26 | 浙江燃创透平机械股份有限公司 | Gas turbine gas flow adjusting structure |
| CN113738453A (en) * | 2021-11-08 | 2021-12-03 | 中国航发四川燃气涡轮研究院 | Turbine guide vane cooling air flow adjusting device |
| CN113738453B (en) * | 2021-11-08 | 2022-02-01 | 中国航发四川燃气涡轮研究院 | Turbine guide vane cooling air flow adjusting device |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Gas turbine turbine gas flow adjusts structure Effective date of registration: 20161104 Granted publication date: 20150923 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20150923 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191224 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: China United heavy-duty gas turbine technology Co., Ltd. Address before: 100084, Beijing, Haidian District science and Technology Park, Tsinghua Science and technology building, block C, 10 Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. |
|
| TR01 | Transfer of patent right |