CN108691577A - The active clearance control structure of turbogenerator - Google Patents
The active clearance control structure of turbogenerator Download PDFInfo
- Publication number
- CN108691577A CN108691577A CN201710228627.6A CN201710228627A CN108691577A CN 108691577 A CN108691577 A CN 108691577A CN 201710228627 A CN201710228627 A CN 201710228627A CN 108691577 A CN108691577 A CN 108691577A
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- CN
- China
- Prior art keywords
- turbine casing
- wall
- inner liner
- burner inner
- control structure
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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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Classifications
-
- 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
- F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
- F01D11/20—Actively adjusting tip-clearance
- F01D11/24—Actively adjusting tip-clearance by selectively cooling-heating stator or rotor components
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
Active clearance control structure of the present invention is related to a kind of turbogenerator, its purpose is to provide one kind under conditions of not changing turbine casing pore size, can adjust the cold air amount by turbine casing stomata, control the active clearance control structure of tip clearance.The active clearance control structure of turbogenerator of the present invention includes burner inner liner and turbine casing, turbo blade is set in turbine casing, it is provided with gas flow optimized part between the outer wall and turbine casing of the burner inner liner, the gas flow optimized part forms inlet channel with the turbine casing gap setting, and the gas flow optimized part is affected by temperature the air inlet port size that can be generated deformation and then adjust the inlet channel;Stomata is opened up on the turbine casing opposite with turbo blade, the stomata is connected to the inlet channel, forms gas channel, and cooling air-flow can flow to the turbo blade by the gas channel.
Description
Technical field
The present invention relates to a kind of turbogenerators, more particularly to a kind of active clearance control structure of turbogenerator.
Background technology
In the combustion chamber of turbogenerator (including turbine aircraft engines and turbine gas turbine), from compressor
High pressure draught and the fuel of penetrating are mixed and burned, and convert the chemical energy of fuel to thermal energy.The combustion gas of high temperature and pressure then pushes
Turbine does work, and converts heat into kinetic energy.In the shutdown process of engine, since the variation of gas temperature can lead to turbine
And turbine casing generates thermal deformation.The wall thickness of turbine casing is much smaller than the diameter of turbine, this can cause two kinds of parts to reach heat
Time needed for stabilization state is very inconsistent.In deformation process, larger turbine blade-tip gap can be such that combustion gas generation lets out
Dew, influences the efficiency of engine;And turbine blade-tip gap is too small, and blade tip and turbine can be caused when engine condition quickly changes
Outer shroud touches mill.
For high pressure draught from compressor other than a part enters burner inner liner participation burning, another part is wrapped in flame
The outer wall of cylinder achievees the purpose that carry out burner inner liner cooling.Later, part cold air can by casing stomata, subsequently into turbine,
Turbine casing and turbo blade are cooled down.In this way, the size of casing stomata directly determines the cold air amount into turbine.
This proposes higher requirement to the processing of casing stomata, and required precision is high, increases processing cost.Simultaneously it is meant that once
The size of casing stomata determines, the cold air amount into turbine is also to determine, unadjustable, cause engine efficiency and can
It is reduced by property.The active clearance control technology of the present invention can control the variation of turbine blade-tip gap, to reduce engine consumption
Oil cut rate improves reliability and prolongs the service life.The key technology of active clearance control is through amount of air entrainment or bleed temperature
Equal parameter adjustments turbine casing Temperature Distribution, to control the radial thermal expansion displacement of turbine casing and turbine outer ring component, to
Control the size of tip clearance.
Invention content
Based on this, the technical problem to be solved in the present invention is to provide a kind of in the condition for not changing turbine casing pore size
Under, the cold air amount by turbine casing stomata, the active clearance control structure of active control tip clearance can be adjusted.
A kind of active clearance control structure of turbogenerator, including burner inner liner and turbine casing, the interior setting of turbine casing
Turbo blade, is provided with gas flow optimized part between the outer wall and turbine casing of the burner inner liner, the gas flow optimized part with it is described
Turbine casing gap setting forms inlet channel, and the gas flow optimized part, which is affected by temperature, can generate described in deformation and then adjusting
The air inlet port size of inlet channel;Stomata is opened up on the turbine casing opposite with turbo blade, the stomata is logical with the air inlet
Road is connected to, and forms gas channel, and cooling air-flow can flow to the turbo blade by the gas channel.
The gas flow optimized part includes the interconnecting piece being connected and the first ring wall, the company in one of the embodiments,
Outer wall of the socket part with the burner inner liner close to outlet end is connect, and first ring wall is arranged along the turbine casing, and to
The direction that the outlet end of the burner inner liner is opposite extends, and inlet channel is formed between first ring wall and the turbine casing;
After first ring wall is affected by temperature, deformation can be generated closer or far from the turbine casing, and then adjust the air inlet
The air inlet port size in channel.
In one of the embodiments, the interconnecting piece include the second ring wall and bending section, second ring wall one end with
The outer wall of the burner inner liner connects, and the second ring wall other end is connect by bending section with first ring wall.
The outer wall of second ring wall and the burner inner liner is detachably connected in one of the embodiments,.
Clamping portion, one end of second ring wall are provided on the outer wall of the burner inner liner in one of the embodiments,
It is inserted into the clamping portion clamping.
Setting support ring flat-plate, the support ring flat-plate and flame on the outer wall of the burner inner liner in one of the embodiments,
The outer wall of cylinder forms the clamping portion, and second ring wall one end is inserted between support ring flat-plate and the outer wall of burner inner liner.
The gas flow optimized part is integrally formed in one of the embodiments,.
The stomata is circumferentially provided at least two rows of along the turbine casing in one of the embodiments,.
Above-mentioned active clearance control structure is the design using gas flow optimized part, flows through the high pressure draught of flame drum outer wall
(cold air) forms shunting.It is learnt by calculating, the rigidity of different temperatures downstream control piece can change.In this way, according to
The change of thermal expansion and contraction principle, fuel gas temperature can make the air inlet of the inlet channel between gas flow optimized part and turbine casing big
Small change, thus to being carried out into the gas flow in blowhole from main regulation, to not change the pore size of turbine casing
Under the conditions of, adjust through the cold air amount of turbine casing stomata, reach adjustment turbine casing Temperature Distribution, control turbine casing and
The radial thermal expansion displacement of turbo blade, to control the purpose of tip clearance.Realize turbine casing and turbine blade-tip gap
Active control, greatly improve the efficiency of engine and the reliability of engine, extend the service life of engine.
Description of the drawings
Fig. 1 is the structural schematic diagram of active clearance control structure of the present invention;
Fig. 2 is the gas channel schematic diagram of active clearance control structure of the present invention;
Reference sign:
The outer wall 100 of burner inner liner;
Turbine casing 200;Stomata 210;
Turbo blade 300;
Gas flow optimized part 400;First ring wall 410;Second ring wall 420;Bending section 430;
Support ring flat-plate 500.
Specific implementation mode
Specific embodiments of the present invention are described in detail below with reference to Figure of description, but the present invention can be with
The multitude of different ways for being defined by the claims and covering is implemented.
Referring to Fig.1, the active clearance control structure of the turbogenerator in one embodiment of the invention, including burner inner liner and
Turbine casing 200 is spaced setting, can make the high pressure gas from compressor between the outer wall 100 and turbine casing 200 of burner inner liner
Flow the outer wall 100 of (cold air) by cooling flame cylinder.Turbo blade 300 is set in turbine casing 200.The outer wall of burner inner liner
Gas flow optimized part 400, gas flow optimized part 400 and 200 gap setting shape of turbine casing are provided between 100 and turbine casing 200
At inlet channel, gas flow optimized part 400 is affected by temperature the air inlet port size that can be generated deformation and then adjust inlet channel.With
Stomata 210 is opened up on the opposite turbine casing 200 of turbo blade 300, stomata 210 is connected to inlet channel, forms gas channel,
Cooling air-flow can flow to turbo blade 300 by gas channel.
Above-mentioned active clearance control structure is the design using gas flow optimized part 400, flows through the outer wall 100 of burner inner liner
High pressure draught (cold air) forms shunting.It is learnt by calculating, the rigidity of different temperatures downstream control piece 400 can change
Become.Therefore, when the change of fuel gas temperature, according to thermal expansion and contraction principle, can make gas flow optimized part 400 and turbine casing 200 it
Between the air inlet of inlet channel vary with temperature and change, realize from main regulation air inflow.To not change turbine casing 200
210 size of stomata under conditions of, adjust through the cold air amount of turbine casing stomata 210, reach 200 temperature of adjustment turbine casing
Degree distribution, controls the radial thermal expansion displacement of turbine casing 200 and turbo blade 300, to control the purpose of tip clearance.It is real
Showed the active control of turbine casing 200 and turbine blade-tip gap, greatly improve engine efficiency and engine can
By property, the service life of engine is extended.
Specifically, gas flow optimized part 400 includes the interconnecting piece and the first ring wall 410 being connected, and interconnecting piece is leaned on burner inner liner
The outer wall connection of nearly outlet end, the first ring wall 410 extend along turbine casing 200, to the direction opposite with the outlet end of burner inner liner,
Inlet channel is formed between first ring wall 410 and turbine casing 200.After first ring wall 410 is affected by temperature, deformation can be generated
Closer or far from turbine casing 200, and then the air inlet port size of inlet channel is adjusted, adjusts the air inflow of gas channel.Due to
First ring wall 410 is thin-wall part, and the first ring wall 410 flows through cold air, the change of fuel gas temperature close to a side surface of burner inner liner
When the first ring wall 410 temperature also change correspondingly, according to thermal expansion and contraction principle, can make the first ring wall 410 and turbine casing 200
Between the air inlet port size of inlet channel that is formed vary with temperature and change, thus allow for from main regulation air inflow.
Further, interconnecting piece includes the second ring wall 420 and bending section 430,420 one end of the second ring wall and burner inner liner it is outer
Wall connects, and 420 other end of the second ring wall is connect by bending section 430 with the first ring wall 410.Second ring wall 420, bending section 430
It is connected as an entirety with the first ring wall 410, section is the winding arc being open towards high pressure draught approach axis, Ke Yiwei
Be integrally formed, can also the second ring wall 420 be integrally formed with bending section 430, the first ring wall 410 is formed with the welding of bending section 430.
First ring wall 410 connect with bending section 430 place section can be arc line shaped or fold-line-shaped, not according to the material of the first ring wall
Together, according to the suitable shape of selection is calculated, when ensureing that the first ring wall is affected by temperature, change the gap between turbine casing
Size.
Still further, the outer wall of the second ring wall 420 and burner inner liner is detachably connected.
Specifically, clamping portion is provided on the outer wall of burner inner liner, clamping portion clamping is inserted into one end of the second ring wall 420.Its
In, setting support ring flat-plate 500 on the outer wall 100 of burner inner liner, the formation of outer wall 100 clamping portion of support ring flat-plate and burner inner liner, second
420 one end of ring wall is inserted between support ring flat-plate 500 and the outer wall 100 of burner inner liner.Second ring wall 420 of gas flow optimized part 400 is logical
It crosses support ring flat-plate 500 to be clamped on the outer wall 100 of burner inner liner, realizes installation.In processing without the outer wall 100 in burner inner liner
Location hole is opened, the processing technology and flow of burner inner liner is greatly simplified, has saved cost.
The quantity of the stomata 210 of the parameter settings turbine casing such as temperature according to high pressure draught, optionally, 210 edge of stomata
Turbine casing is circumferentially disposed at least two rows of.
The operation principle of above-mentioned active clearance control structure is as follows, and wherein hollow arrow is blower outlet air-flow, solid
Arrow is combustor exit air-flow:
High pressure draught from blower outlet is filled with the cavity that the outer wall 100 of burner inner liner is formed with turbine casing 200
In.
A part of high pressure draught enters burner inner liner and participates in burning, and the high-temperature high-pressure air flow of formation is flowed out from combustor exit,
Then push gas turbine acting.
The high pressure draught that another part does not enter into burner inner liner is divided by the first ring wall 410 of burner inner liner gas flow optimized part 400
Stream, turbo blade 300 is flowed to by gas channel.As shown in Fig. 2, 410 He of the first ring wall that air-flow passes through gas flow optimized part 400
The inlet channel that turbine casing 200 is formed, then, air-flow cool down turbine leaf by the stomata 210 on turbine casing 200
Piece 300.
In engine temperature ascent stage, since the first ring wall 410 of gas flow optimized part 400 is thin-wall part, temperature distortion
One end is opened far from turbine casing afterwards, and the gap between the first ring wall 410 and turbine casing 200 of gas flow optimized part 400 becomes
Greatly, i.e., air inlet becomes larger so that becomes more by the cooling air of turbine casing stomata 210.In this way, turbine casing can be reduced
200 temperature rise rate, reduces the thermal deformation rate of turbine casing 200, and control turbine casing 200 becomes larger with turbine blade-tip gap.
In the engine temperature decline stage, between the first ring wall 410 and turbine casing 200 of gas flow optimized part 400 between
Gap reduces with temperature drop, i.e., air inlet becomes smaller so that is tailed off by the cooling air of turbine casing stomata 210.In this way, can be with
The temperature drop rate of turbine casing 200 is reduced, reduces the contraction rate of turbine casing 200, prevents turbine casing 200 and turbine blade-tip
Gap is too small.
Using the turbogenerator of above-mentioned active clearance control structure, the master of turbine casing and turbine blade-tip gap is realized
Dynamic control, greatly improves the efficiency of engine and the reliability of engine, extends the service life of engine.
Several embodiments of the invention above described embodiment only expresses, the description thereof is more specific and detailed, but simultaneously
Cannot the limitation to the scope of the claims of the present invention therefore be interpreted as.It should be pointed out that for those of ordinary skill in the art
For, without departing from the inventive concept of the premise, various modifications and improvements can be made, these belong to the guarantor of the present invention
Protect range.Therefore, the protection domain of patent of the present invention should be determined by the appended claims.
Claims (8)
1. a kind of active clearance control structure of turbogenerator, including burner inner liner and turbine casing, turbine casing is interior to be arranged whirlpool
Impeller blade, which is characterized in that gas flow optimized part, the gas flow optimized are provided between the outer wall and turbine casing of the burner inner liner
Part forms inlet channel with the turbine casing gap setting, and the gas flow optimized part, which is affected by temperature, can generate deformation in turn
Adjust the air inlet port size of the inlet channel;Stomata, the stomata and institute are opened up on the turbine casing opposite with turbo blade
Inlet channel connection is stated, gas channel is formed, cooling air-flow can flow to the turbo blade by the gas channel.
2. the active clearance control structure of turbogenerator according to claim 1, which is characterized in that the gas flow optimized
Part includes the interconnecting piece being connected and the first ring wall, and outer wall of the interconnecting piece with the burner inner liner close to outlet end is connect, institute
It states the first ring wall along the turbine casing to be arranged, and extends to the direction opposite with the outlet end of the burner inner liner, described the
Inlet channel is formed between one ring wall and the turbine casing;After first ring wall is affected by temperature, deformation can be generated and leaned on
Close or remote from the turbine casing, and then adjust the air inlet port size of the inlet channel.
3. the active clearance control structure of turbogenerator according to claim 2, which is characterized in that the interconnecting piece packet
The second ring wall and bending section are included, second ring wall one end is connect with the outer wall of the burner inner liner, the second ring wall other end
It is connect with first ring wall by bending section.
4. the active clearance control structure of turbogenerator according to claim 3, which is characterized in that second ring wall
It is detachably connected with the outer wall of the burner inner liner.
5. the active clearance control structure of turbogenerator according to claim 4, which is characterized in that the burner inner liner
Clamping portion is provided on outer wall, the clamping portion clamping is inserted into one end of second ring wall.
6. the active clearance control structure of turbogenerator according to claim 5, which is characterized in that the burner inner liner
The outer wall of setting support ring flat-plate on outer wall, the support ring flat-plate and burner inner liner forms the clamping portion, second ring wall one end
It is inserted between support ring flat-plate and the outer wall of burner inner liner.
7. the active clearance control structure of turbogenerator according to claim 6, which is characterized in that the gas flow optimized
Part is integrally formed.
8. the active clearance control structure of turbogenerator according to claim 1, which is characterized in that the stomata is along institute
It states turbine casing and is circumferentially provided at least two rows.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710228627.6A CN108691577B (en) | 2017-04-10 | 2017-04-10 | The active clearance control structure of turbogenerator |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710228627.6A CN108691577B (en) | 2017-04-10 | 2017-04-10 | The active clearance control structure of turbogenerator |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN108691577A true CN108691577A (en) | 2018-10-23 |
| CN108691577B CN108691577B (en) | 2019-09-20 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710228627.6A Active CN108691577B (en) | 2017-04-10 | 2017-04-10 | The active clearance control structure of turbogenerator |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111927579A (en) * | 2020-07-31 | 2020-11-13 | 中国航发贵阳发动机设计研究所 | Thermal deformation adjusting structure and method for turbine case |
| CN114278401A (en) * | 2020-09-28 | 2022-04-05 | 中国航发商用航空发动机有限责任公司 | Turbine casing of turbine engine and turbine engine |
| CN114396324A (en) * | 2021-12-27 | 2022-04-26 | 哈尔滨工程大学 | Shrouded blade with casing having cooling channel-groove seal-bendable sealing strip composite structure |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6116852A (en) * | 1997-12-11 | 2000-09-12 | Pratt & Whitney Canada Corp. | Turbine passive thermal valve for improved tip clearance control |
| EP1890010A2 (en) * | 2006-08-10 | 2008-02-20 | United Technologies Corporation | Ceramic turbine shroud assembly |
| US20110179805A1 (en) * | 2010-01-28 | 2011-07-28 | Bruno Chatelois | Rotor containment structure for gas turbine engine |
-
2017
- 2017-04-10 CN CN201710228627.6A patent/CN108691577B/en active Active
Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6116852A (en) * | 1997-12-11 | 2000-09-12 | Pratt & Whitney Canada Corp. | Turbine passive thermal valve for improved tip clearance control |
| EP1890010A2 (en) * | 2006-08-10 | 2008-02-20 | United Technologies Corporation | Ceramic turbine shroud assembly |
| US20110179805A1 (en) * | 2010-01-28 | 2011-07-28 | Bruno Chatelois | Rotor containment structure for gas turbine engine |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111927579A (en) * | 2020-07-31 | 2020-11-13 | 中国航发贵阳发动机设计研究所 | Thermal deformation adjusting structure and method for turbine case |
| CN111927579B (en) * | 2020-07-31 | 2022-09-06 | 中国航发贵阳发动机设计研究所 | Thermal deformation adjusting structure and method for turbine case |
| CN114278401A (en) * | 2020-09-28 | 2022-04-05 | 中国航发商用航空发动机有限责任公司 | Turbine casing of turbine engine and turbine engine |
| CN114278401B (en) * | 2020-09-28 | 2024-04-26 | 中国航发商用航空发动机有限责任公司 | Turbine casing of turbine engine and turbine engine |
| CN114396324A (en) * | 2021-12-27 | 2022-04-26 | 哈尔滨工程大学 | Shrouded blade with casing having cooling channel-groove seal-bendable sealing strip composite structure |
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| Publication number | Publication date |
|---|---|
| CN108691577B (en) | 2019-09-20 |
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