CN105971674A - Gas turbine rim sealing structure and method - Google Patents
Gas turbine rim sealing structure and method Download PDFInfo
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- CN105971674A CN105971674A CN201610614170.8A CN201610614170A CN105971674A CN 105971674 A CN105971674 A CN 105971674A CN 201610614170 A CN201610614170 A CN 201610614170A CN 105971674 A CN105971674 A CN 105971674A
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- stator blade
- cooling
- gas turbine
- platform
- chamber
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
- F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
- F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention relates to the technical field of gas turbines, in particular to a gas turbine rim sealing structure. The structure comprises a static vane connected to a static vane platform and a movable vane connected to a movable vane platform, wherein an airtight cool air channel is formed between the static vane platform and the movable vane platform, blowing holes are formed in the peripheral direction of the static vane platform and communicated with a static vane cooling channel, an outlet of each blow hole is located on the downstream side of the static vane platform and communicated with the airtight cool air channel, and the blow holes are used for guiding cooling air in the cooling channel out and making cooling air form an air curtain at the position of an outlet of the airtight cool air channel. The invention further relates to a rim sealing method. By the adoption of the method, cooling air in the static vane cooling channel can be guided out from the downstream side of the static vane platform, and the air curtain can be formed by cooling air at the position of the outlet of the airtight cool air channel. The air curtain can improve the airtight performance of the gas turbine rim sealing structure, reduce airtight cool air amount, reduce the influence of airtight cool air on aerodynamic efficiency of main current, and improve overall efficiency.
Description
Technical field
The present invention relates to gas turbine technology field, particularly relate to a kind of gas turbine wheel rim and seal structure and method.
Background technology
Heavy duty gas turbine mainly includes compressor, combustor and the big parts of turbine three.Air is compressed into height after entering compressor
The air of temperature high pressure, supply chamber fuel burning, the high-temperature high-pressure fuel gas of generation expansion work in turbine, then through aerofluxus
Diffuser enters the equipment such as air or waste heat boiler.
After the main flow runner high-temperature fuel gas of turbine flows through stator blade ,-quiet parts zone line circumferentially alternating formation high-pressure flow can turned
District and low pressure flow region.Turning quiet dish chamber internal pressure because of main flow flowpath pressure higher than turbine at high-pressure flow district, this is induction
One of reason of high-temperature fuel gas invasion phenomenon.Its two, turn the rotational flow in quiet dish intracavity portion and make to turn quiet dish intracavity and there is radially pressure
Power gradient, the pressure in wheel disc space is less than outside, and this also can induce high-temperature fuel gas invasion phenomenon.Research shows that combustion gas invasion is existing
As if cause the key factor of turbine wheel disc overheating failure.Turbine wheel disc overheating failure problem, mesh is caused for combustion gas invasion phenomenon
Front main flow heavy duty gas turbine manufacturer mainly obturage cold to turning a quiet dish chamber by introducing high pressure cooling air-flow from compressor stage
But and the measure such as wheel rim sealing of advanced configuration is installed solves combustion gas invasion problem.But the flow of cold air of obturaging is excessive, meeting
Having a strong impact on overall efficiency, research shows, reduces by the air conditioning quantity of obturaging of 50%, and the overall efficiency of gas turbine can improve about
0.3%.
At present, practical engineering application generally uses radial flange seal the method replacing traditional axial flange, can not send out
Air conditioning quantity of obturaging is reduced on the premise of raw combustion gas invasion phenomenon, but only by arranging the radial flange sealing minimizing to air conditioning quantity of obturaging
Limitation；And cold air of obturaging directly enters main flow runner with 90 ° of directions, also can adversely affect main flow pneumatic efficiency.
Summary of the invention
The technical problem to be solved in the present invention is to provide one and can effectively reduce air conditioning quantity of obturaging, reduce and obturage cold air to main flow gas
The gas turbine wheel rim of efficiency of movement impact seals structure and method, to overcome the drawbacks described above of prior art.
In order to solve above-mentioned technical problem, the present invention adopts the following technical scheme that a kind of gas turbine wheel rim seals structure, including
The stator blade being connected on stator blade platform and the movable vane being connected on movable vane platform, between stator blade platform and movable vane platform, formation is obturaged cold
Gas passage, along the fumarole that is circumferentially with of stator blade platform, fumarole is connected with the cooling duct of stator blade, the outlet position of fumarole
Being connected in the downstream of stator blade platform and with cold air path of obturaging, fumarole is for deriving the cooling gas in cooling duct and making
Cooling gas forms air curtain in the exit of cold air path of obturaging.
Preferably, being additionally provided with a chamber at stator blade platform interior, chamber is connected with cooling duct and fumarole.
Preferably, in stator blade platform, it is provided with a baffle plate, between the top board of baffle plate and stator blade platform, forms chamber.
Preferably, in chamber, be provided with a shock plate, shock plate chamber is separated into the top board away from stator blade platform pressure chamber and
Near the impinging cooling chamber of top board of stator blade platform, and offer multiple by pressure chamber and impinging cooling chamber phase on shock plate
The impact opening of connection；Pressure chamber is connected with cooling duct, and impinging cooling chamber is connected with fumarole.
Preferably, the angle between exit flow direction and the exit flow direction of stator blade of fumarole is less than 30 °.
Preferably, the section configuration of the outlet of fumarole is circular or rectangle.
Preferably, the outer rim of stator blade platform has towards the depression flexure plane turning quiet dish chamber, and the outer rim of movable vane platform has towards master
The convex curved face of stream runner, the formation that matches with convex curved face of depression flexure plane is obturaged cold air path.
A kind of gas turbine wheel rim encapsulating method, derives the cooling gas stator blade cooling duct from the downstream of stator blade platform, and
Cooling gas is made to form air curtain in the exit of cold air path of obturaging.
Preferably, cooling gas is made to derive from the downstream of stator blade platform after stator blade platform carries out impinging cooling again.
Preferably, be passed through, in cold air path of obturaging, cold air of obturaging, the cold air that makes to obturage mix with air curtain laggard enter main flow runner.
Compared with prior art, the present invention has the most progressive:
By the cooling gas in stator blade cooling duct is derived and in the exit obturaging cold air path from the downstream of stator blade platform
Forming air curtain, this air curtain acts not only as the barrier stoping the high-temperature fuel gas invasion of main flow runner to turn quiet dish chamber, effectively reduces height
Temperature combustion gas Invasive degree, improves gas turbine wheel rim and seals the seal performance of structure, thus realize, in guarantee, turbine wheel disc does not occur
Reduce, on the premise of crossing hot injury, air conditioning quantity of obturaging；The cold air of obturaging obturaging in cold air path can also be changed and enter main flow runner
Direction, the cold air that makes to obturage enters main flow runner with the direction less with the main flow direction angle of main flow runner and mixes with high-temperature fuel gas,
Thus reduce mixing loss, reduce the cold air impact on main flow pneumatic efficiency of obturaging；Additionally, this air curtain is by the cooling gas of stator blade
Formed, substantially the recycling to stator blade cooling gas, can greatly save the use total amount of complete machine cooling gas.Thus, adopt
Seal structure and method with the gas turbine wheel rim of the present invention, the overall efficiency of gas turbine can be dramatically increased, improve combustion gas wheel
The security and stability that machine runs.
Accompanying drawing explanation
Fig. 1 is the cross-sectional schematic of the gas turbine wheel rim sealing structure of the embodiment of the present invention.
Fig. 2 is the enlarged diagram in A portion in Fig. 1.
Fig. 3 is the schematic diagram that the fumarole exit flow direction of the embodiment of the present invention becomes angle with stator blade exit flow direction.
In figure:
1, stator blade platform 101, top board 2, movable vane platform
3, stator blade 4, movable vane 5, turn quiet dish chamber
6, obturage cold air path 7, fumarole 8, cooling duct
9, chamber 10, baffle plate 11, shock plate
12, pressure chamber 13, impinging cooling chamber 14, impact opening
15, depression flexure plane 16, convex curved face
A, the exit flow direction b of stator blade, the exit flow direction of fumarole
α, angle between the exit flow direction of fumarole and the exit flow direction of stator blade
Detailed description of the invention
Below in conjunction with the accompanying drawings the detailed description of the invention of the present invention is described in further detail.These embodiments are merely to illustrate this
Invention, and not limitation of the present invention.
In describing the invention, it should be noted that term " " center ", " longitudinally ", " laterally ", " on ", D score, " front ",
Orientation or the position relationship of the instruction such as " afterwards ", "left", "right", " vertically ", " level ", " top ", " end " " interior ", " outward " are
Based on orientation shown in the drawings or position relationship, it is for only for ease of the description present invention and simplifies description rather than instruction or hint
The device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore it is not intended that to this
Bright restriction.Additionally, term " first ", " second " are only used for describing purpose, and it is not intended that instruction or imply relatively heavy
The property wanted.
In describing the invention, it should be noted that unless otherwise clearly defined and limited, term " install ", " being connected ",
" connect " and should be interpreted broadly, connect for example, it may be fixing, it is also possible to be to removably connect, or be integrally connected；Can
To be mechanical connection, it is also possible to be electrical connection；Can be to be joined directly together, it is also possible to be indirectly connected to by intermediary, Ke Yishi
The connection of two element internals.For the ordinary skill in the art, can understand that above-mentioned term exists as the case may be
Concrete meaning in the present invention.
Additionally, in describing the invention, except as otherwise noted, " multiple " are meant that two or more.
As depicted in figs. 1 and 2, present embodiments provide a kind of gas turbine wheel rim and seal structure.As it is shown in figure 1, this enforcement
The gas turbine wheel rim of example seals structure and includes stator blade platform 1, stator blade 3, movable vane platform 2 and movable vane 4.Those skilled in the art
Known, in the turbine assembly of gas turbine, stator blade 3 is connected on stator blade platform 1, and movable vane 4 is connected to movable vane platform 2
On, formed between movable vane wheel disc and stator and turn quiet dish chamber 5, between stator blade platform 1 and movable vane platform 2, form cold air path 6 of obturaging,
Cold air path of obturaging makes to turn quiet dish chamber 5 and is connected with main flow runner, is passed through, in turning quiet dish chamber 5, cold air of obturaging, cold air warp of obturaging
Cold air path 6 of obturaging enters main flow runner, the high-temperature fuel gas in main flow runner can be stoped to intrude into and turn in quiet dish chamber 5.
As in figure 2 it is shown, the stator blade platform 1 of the present embodiment is provided with multiple fumarole 7, multiple fumaroles 7 are along the week of stator blade platform 1
To distribution.The entrance of fumarole 7 is positioned at the upstream side of stator blade platform 1 and is connected with the cooling duct 8 of stator blade 3, fumarole
The outlet of 7 is positioned at the downstream of stator blade platform 1 and is connected with cold air path 6 of obturaging so that fumarole 7 can be logical by cooling
Cooling gas in road 8 is derived to cold air path 6 of obturaging, and makes the cooling gas of derivation in the exit obturaging cold air path 6
Form air curtain.This air curtain is being obturaged between cold air path 6 and main flow runner, acts not only as stoping the high temperature of main flow runner
Combustion gas invasion turns the barrier in quiet dish chamber 5, effectively reduces high-temperature fuel gas Invasive degree, improves gas turbine wheel rim and seals the envelope of structure
Tight performance, thus realize reducing, on the premise of ensureing the overheated damage of turbine wheel disc, air conditioning quantity of obturaging；Envelope can also be changed
Cold air of obturaging in tight cold air path 6 enters the direction of main flow runner, makes to obturage cold air with the main flow direction angle with main flow runner
Less direction enters main flow runner and mixes with high-temperature fuel gas, thus reduces mixing loss, reduces cold air effect pneumatic to main flow of obturaging
The impact of rate；Additionally, this air curtain is formed by the cooling gas of stator blade 3, substantially stator blade 3 is cooled down the recycling of gas,
Can greatly save the use total amount of complete machine cooling gas.Thus, the gas turbine wheel rim of the present embodiment is used to seal structure, can
To dramatically increase the overall efficiency of gas turbine, to improve the security and stability of gas turbine operation.
It should be noted that " upstream " and " downstream " herein, be with the main flow direction of main flow runner as reference for, main
The main flow direction of stream runner is the exit flow direction a of stator blade.
In the present embodiment, the preferably exit flow direction b of the fumarole 7 and exit flow direction a of stator blade is parallel, to be formed
The air curtain paralleled with main flow runner, makes effect optimum of obturaging.Certainly, the exit flow direction b of fumarole 7 can also deviate
Main flow runner, but in order to ensure that the air curtain formed can produce the effect of effectively obturaging, the outlet of fumarole 7 to turning quiet dish chamber 5
The angle of airflow direction b deviation main flow runner is unsuitable excessive.As it is shown on figure 3, the exit flow direction b of fumarole 7 and stator blade
Angle α between the exit flow direction a of 3 should be less than 30 °, so that air curtain can stop the high temperature combustion of main flow runner effectively
Gas.The section configuration of the outlet of fumarole 7 is not limited to, and can be circular or rectangle.The diameter of fumarole 7 then may be used
According to the main flow temperature in actual gas turbine unit, mainstream speed, cooling gas temperature and fumarole 7 and gas turbine axle
The parameters such as the distance between line are configured.The quantity of fumarole 7 is not limited to, and can enter according to the parameter of actual gas turbine group
Row is arranged.
Further, in the present embodiment, inside stator blade platform 1, a chamber 9, chamber 9 and cooling duct 8 and jet it are additionally provided with
Hole 7 is connected.Cooling gas in cooling duct 8 is first passed through in chamber 9, to keep the pressure of cooling gas, then by jet
Hole 7 is derived, and advantageously forms high pressure air curtain, thus can obtain effect of preferably obturaging.The present embodiment sets in stator blade platform 1
There is a baffle plate 10, between the top board 101 of baffle plate 10 and stator blade platform 1, form chamber 9.
Further, in the present embodiment, in order to improve the utilization rate of cooling gas, strengthen cooling effect, it is provided with in chamber 9
One shock plate 11, shock plate 11 be arranged in parallel with baffle plate 10, and chamber 9 is separated into away from stator blade platform 1 by shock plate 11
The pressure chamber 12 of top board 101 and the impinging cooling chamber 13 of the top board 101 near stator blade platform 1, i.e. shock plate 11 and gear
Form pressure chamber 12 between plate 10, between the top board 101 of shock plate 11 and stator blade platform 1, form impinging cooling chamber 13.
Multiple impact opening 14 pressure chamber 12 being connected, pressure chamber 12 is offered with impinging cooling chamber 13 on shock plate 11
Being connected with cooling duct 8, impinging cooling chamber 13 is connected with the entrance of fumarole 7.Arrow in Fig. 2 shows cooling
What gas flow to obturage cold air path 6 from cooling duct 8 flows through route, specifically, the cooling gas in cooling duct 8 first leads to
Entering in pressure chamber 12, then the impact opening 14 from shock plate 11 enters impinging cooling chamber 13 and impacts stator blade platform 1
Top board 101, it is achieved the impinging cooling to stator blade platform 1, derived by fumarole 7 the most again, formed high pressure air curtain.Thus,
While cooling gas in realizing stator blade 3 cooling duct 8 carries out impinging cooling to stator blade platform 1, it is also possible to obtain further
More preferable air curtain is obturaged effect, thus improve overall efficiency further.
In the present embodiment, on shock plate 11, quantity and the size of impact opening 14 are not limited to, it is preferable that can on shock plate 11
To be provided with 60-80 impact opening 14, the diameter of impact opening 14 can be set to 0.6-2mm.
Further, enter the direction of main flow runner in order to preferably change the cold air of obturaging obturaging in cold air path 6, subtract further
Little cold air of obturaging enters the angle between direction and the main flow direction of main flow runner of main flow runner, the stator blade platform in the present embodiment
The outer rim of 1 has towards the depression flexure plane 15 turning quiet dish chamber 5, and the outer rim of movable vane platform 2 has the projection towards main flow runner
Flexure plane 16, the formation that matches with convex curved face 16 of depression flexure plane 15 is obturaged cold air path 6.The cold air so that obturage
The main flow direction flowing to relative main flow runner in cold air path 6 of obturaging acutangulates inclination (as shown by the arrows in Figure 2), passes through
The effect of air curtain then can make this acute rake angle reduce further, therefore, it is possible to preferably reduce mixing loss, reduce cold air pair of obturaging
The impact of main flow pneumatic efficiency.
The present embodiment additionally provides a kind of gas turbine wheel rim encapsulating method.As depicted in figs. 1 and 2, the wheel rim of the present embodiment is close
Encapsulation method is: derives the cooling gas stator blade cooling duct 8 from the downstream of stator blade platform 1, and makes this cooling gas in envelope
The exit of tight cold air path 6 forms air curtain.Be passed through, in cold air path 6 of obturaging, cold air of obturaging, make to obturage cold air with obturage cold
The air curtain in gas passage 6 exit meet mixing laggard enter main flow runner.Preferably, the cooling gas in stator blade cooling duct 8 is made
First it is passed through in the chamber 9 within stator blade platform 1 and forms and keep pressure, then derive from the downstream of stator blade platform 1, form height
Calm the anger curtain.More preferably, the cooling gas in stator blade cooling duct 8 is made first to be passed through in the chamber 9 within stator blade platform 1 and to quiet
After leaf platform 1 carries out impinging cooling, then derive from the downstream of stator blade platform 1.Further, make cooling gas from stator blade platform
Angle between 1 airflow direction and the exit flow direction of stator blade derived is less than 30 °.
The gas turbine wheel rim encapsulating method of the present embodiment can seal structure by the gas turbine wheel rim of the present invention and realize.
In sum, the gas turbine wheel rim of the present embodiment seals structure and method, by by the cooling in stator blade cooling duct 8
Gas from the downstream of stator blade platform 1 derive and obturage between cold air path 6 and main flow runner formed air curtain, it is possible to realize with
Lower effect:
(1) this air curtain turns the barrier in quiet dish chamber 5 as the high-temperature fuel gas invasion stoping main flow runner, it is possible to effectively reduce high temperature combustion
Gas Invasive degree, improves gas turbine wheel rim and seals the seal performance of structure, thus realize not occurring turbine wheel disc overheated in guarantee
Reduce air conditioning quantity of obturaging on the premise of damage, and then improve the overall efficiency of gas turbine.
(2) this air curtain can change the cold air of obturaging obturaging in cold air path 6 and enters the direction of main flow runner, make to obturage cold air with
The direction less with the main flow direction angle of main flow runner enters main flow runner and mixes with high-temperature fuel gas, thus reduce mixing loss,
Reduce the obturage cold air impact on main flow pneumatic efficiency, the beneficially lifting of overall efficiency.
(3) this air curtain is formed by the cooling gas of stator blade 3, and stator blade 3 substantially cools down the recycling of gas, can greatly save
The about use total amount of complete machine cooling gas, thus the lifting of beneficially overall efficiency.
Below it is only the preferred embodiment of the present invention, it is noted that for those skilled in the art,
On the premise of the technology of the present invention principle, it is also possible to make some improvement and replacement, these improve and replace and also should be regarded as this
The protection domain of invention.
Claims (10)
1. gas turbine wheel rim seals a structure, including the stator blade (3) being connected on stator blade platform (1) with to be connected to movable vane flat
Movable vane (4) on platform (2), forms cold air path of obturaging between described stator blade platform (1) and described movable vane platform (2)
(6), it is characterised in that be circumferentially with fumarole (7) along described stator blade platform (1), described fumarole (7) with
The cooling duct (8) of described stator blade (3) is connected, and the outlet of described fumarole (7) is positioned at described stator blade platform (1)
Downstream and be connected with described cold air path of obturaging (6), described fumarole (7) is used for deriving described cooling duct
(8) cooling gas in also makes described cooling gas form air curtain in the exit of described cold air path of obturaging (6).
Gas turbine wheel rim the most according to claim 1 seals structure, it is characterised in that internal described stator blade platform (1)
Being additionally provided with a chamber (9), described chamber (9) is connected with described cooling duct (8) and fumarole (7).
Gas turbine wheel rim the most according to claim 2 seals structure, it is characterised in that be provided with in described stator blade platform (1)
One baffle plate (10), forms described chamber between the top board (101) of described baffle plate (10) and described stator blade platform (1)
(9)。
Gas turbine wheel rim the most according to claim 2 seals structure, it is characterised in that described chamber is provided with a punching in (9)
Hitting plate (11), described chamber (9) is separated into the top board (101) away from described stator blade platform (1) by described shock plate (11)
Pressure chamber (12) and near the impinging cooling chamber (13) of top board (101) of described stator blade platform (1), and institute
State to offer on shock plate (11) and multiple described pressure chamber (12) is connected with described impinging cooling chamber (13)
Impact opening (14)；Described pressure chamber (12) is connected with described cooling duct (8), described impinging cooling chamber
(13) it is connected with described fumarole (7).
Gas turbine wheel rim the most according to claim 1 seals structure, it is characterised in that working off one's feeling vent one's spleen of described fumarole (7)
Angle between exit flow direction (a) of flow path direction (b) and described stator blade (3) is less than 30 °.
Gas turbine wheel rim the most according to claim 1 seals structure, it is characterised in that the outlet of described fumarole (7)
Section configuration is circular or rectangle.
Gas turbine wheel rim the most according to claim 1 seals structure, it is characterised in that the outer rim of described stator blade platform (1)
Having towards the depression flexure plane (15) turning quiet dish chamber (5), the outer rim of described movable vane platform (2) has towards main current flow
The convex curved face (16) in road, described depression flexure plane (15) is matched with described convex curved face (16) described in formation
Obturage cold air path (6).
8. a gas turbine wheel rim encapsulating method, it is characterised in that derive stator blade cooling duct from the downstream of stator blade platform
Cooling gas, and make described cooling gas form air curtain in the exit of cold air path of obturaging.
Gas turbine wheel rim encapsulating method the most according to claim 8, it is characterised in that make described cooling gas to described quiet
Leaf platform is derived from the downstream of described stator blade platform after carrying out impinging cooling again.
Gas turbine wheel rim encapsulating method the most according to claim 8, it is characterised in that logical in described cold air path of obturaging
Enter cold air of obturaging, make described in obturage cold air mix with described air curtain laggard enter main flow runner.
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| CN201610614170.8A CN105971674B (en) | 2016-07-29 | 2016-07-29 | Gas turbine wheel rim sealing structure and method |
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| CN201610614170.8A CN105971674B (en) | 2016-07-29 | 2016-07-29 | Gas turbine wheel rim sealing structure and method |
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| CN105971674B CN105971674B (en) | 2018-04-03 |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108060979A (en) * | 2017-12-19 | 2018-05-22 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and its swirl-flow devices |
| CN108071492A (en) * | 2017-12-19 | 2018-05-25 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and its part flow arrangement of prewhirling |
| CN110608069A (en) * | 2018-06-14 | 2019-12-24 | 中国联合重型燃气轮机技术有限公司 | Method for selecting turbine rim sealing structure |
| CN111237017A (en) * | 2020-02-17 | 2020-06-05 | 杭州汽轮动力集团有限公司 | Sealing and heat-dissipating structure for gas turbine interstage |
| CN111794807A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | Power turbine inlet guider for fuel-drive compressor unit |
| CN113586251A (en) * | 2021-07-22 | 2021-11-02 | 西安交通大学 | Part cooling-wheel rim sealing structure for stepwise utilization of cooling airflow of gas turbine |
| CN114320489A (en) * | 2022-01-11 | 2022-04-12 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
| CN114486222A (en) * | 2022-01-26 | 2022-05-13 | 沈阳航空航天大学 | Composite experimental device for movable blade heat engine of air seal type gas turbine |
| CN114961870A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine rim sealing system and aeroengine |
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| CN108060979B (en) * | 2017-12-19 | 2024-04-26 | 中国联合重型燃气轮机技术有限公司 | Gas turbine and swirling device thereof |
| CN110608069B (en) * | 2018-06-14 | 2022-03-25 | 中国联合重型燃气轮机技术有限公司 | Method for selecting turbine rim sealing structure |
| CN110608069A (en) * | 2018-06-14 | 2019-12-24 | 中国联合重型燃气轮机技术有限公司 | Method for selecting turbine rim sealing structure |
| CN111237017A (en) * | 2020-02-17 | 2020-06-05 | 杭州汽轮动力集团有限公司 | Sealing and heat-dissipating structure for gas turbine interstage |
| CN111237017B (en) * | 2020-02-17 | 2024-06-07 | 杭州汽轮控股有限公司 | Interstage sealing heat radiation structure of gas turbine |
| CN111794807A (en) * | 2020-06-24 | 2020-10-20 | 中船重工龙江广瀚燃气轮机有限公司 | Power turbine inlet guider for fuel-drive compressor unit |
| CN114961870A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine rim sealing system and aeroengine |
| CN114961872A (en) * | 2021-02-24 | 2022-08-30 | 中国航发商用航空发动机有限责任公司 | Aeroengine rim sealing system and aeroengine |
| CN113586251A (en) * | 2021-07-22 | 2021-11-02 | 西安交通大学 | Part cooling-wheel rim sealing structure for stepwise utilization of cooling airflow of gas turbine |
| CN113586251B (en) * | 2021-07-22 | 2023-03-14 | 西安交通大学 | Part cooling-wheel rim sealing structure for stepwise utilization of cooling airflow of gas turbine |
| CN114320489A (en) * | 2022-01-11 | 2022-04-12 | 永旭腾风新能源动力科技（北京）有限公司 | Gas turbine with gas seal component |
| CN114486222A (en) * | 2022-01-26 | 2022-05-13 | 沈阳航空航天大学 | Composite experimental device for movable blade heat engine of air seal type gas turbine |
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