CN103089451A - Thermal-protection cover - Google Patents
Thermal-protection cover Download PDFInfo
- Publication number
- CN103089451A CN103089451A CN2013100204466A CN201310020446A CN103089451A CN 103089451 A CN103089451 A CN 103089451A CN 2013100204466 A CN2013100204466 A CN 2013100204466A CN 201310020446 A CN201310020446 A CN 201310020446A CN 103089451 A CN103089451 A CN 103089451A
- Authority
- CN
- China
- Prior art keywords
- ring
- cover plate
- sealing gland
- insulation cover
- heat
- Prior art date
- 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.)
- Granted
Links
- 210000004907 gland Anatomy 0.000 claims description 49
- 238000007789 sealing Methods 0.000 claims description 49
- 239000007789 gas Substances 0.000 claims description 39
- 238000009413 insulation Methods 0.000 claims description 31
- 239000011148 porous material Substances 0.000 claims description 29
- 239000000567 combustion gas Substances 0.000 claims description 17
- 230000002093 peripheral effect Effects 0.000 claims description 9
- 238000005476 soldering Methods 0.000 claims description 8
- 238000003466 welding Methods 0.000 claims description 7
- 230000015572 biosynthetic process Effects 0.000 claims description 6
- 238000010304 firing Methods 0.000 claims description 3
- 239000002737 fuel gas Substances 0.000 claims description 3
- 230000008676 import Effects 0.000 claims description 3
- 230000001936 parietal effect Effects 0.000 claims description 3
- 210000000515 tooth Anatomy 0.000 claims description 3
- 238000002485 combustion reaction Methods 0.000 abstract description 5
- 238000009434 installation Methods 0.000 abstract description 4
- 230000008901 benefit Effects 0.000 abstract description 3
- 238000010438 heat treatment Methods 0.000 abstract description 2
- 230000007613 environmental effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 7
- 238000013461 design Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- 230000003068 static effect Effects 0.000 description 4
- 238000012546 transfer Methods 0.000 description 4
- 230000006872 improvement Effects 0.000 description 2
- 230000014793 stomatal movement Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 230000001360 synchronised effect Effects 0.000 description 1
Images
Landscapes
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a heat end part thermal-protection cover in a gas collection shell of a gas turbine. The thermal-protection cover comprises an air seal ring, a clamping ring, a thermal-protection cover plate and an installation side, wherein the air seal ring is inlaid at the inner ring of the clamping ring, and the side face of the clamping ring is fixed by a flange; the clamping ring and the thermal-protection cover plate are welded along the periphery, the thermal-protection cover plate and the installation side are welded along the periphery, and the installation side and a combustion engine shell are connected through bolts; a plurality of rows of radial air holes are distributed on the thermal-protection cover plate along the axial direction, each row of air holes are uniform distributed along the periphery, and the quantity of the air holes is adjusted according to need; and the circumferential included angle among the air holes is zero or not zero. The heat end part thermal-protection cover provided by the invention has the advantages that the structure is simple, the cost is low, the hot end part of the combustion engine can superheat compressed air in the gas collection shell to be effectively reduced, and the environmental temperature of a shafting part is prevented from overtopping, so that a heating invalidation failure is generated.
Description
Technical field
The invention belongs to gas turbine general structure design field, relate to hot-end component heat shield structure in a kind of gas turbine gas collection housing.Specifically, be a kind of thermal shield that is used in combustion turbine exhaustion section heating part.
Background technique
In 100KW level gas turbine general structure layout, combustion gas volute, turbine exhaust section, pressurized air, rotor casing are wrapped in the gas collection housing jointly.Not overheated for guaranteeing the shafting components ambient temperature, pressurized air is remained in rational temperature range before participating in burning, be necessary to control hot-end component to compressed-air actuated heat output.State's internal-combustion engine design experiences still lacks, especially for design, the improvement of general structure, not and the advanced design theory synchronous, have narrow limitation.Existing heat-insulating technique can not prevent effectively that pressurized air is overheated and keep the harmony in temperature field in the gas collection housing, easily causes shafting components overheated, causes the thermal failure fault, then can not guarantee stability, the reliability of working rotor, has affected its working life.
Summary of the invention
The object of the invention is to the shortcoming and defect for existing heat-insulating technique, a kind of heat shield structure is proposed, overheated effectively to prevent pressurized air, be beneficial to the harmony of keeping temperature field in the gas collection housing, prevent that shafting components is overheated, guarantee stability, the reliability of working rotor, extend its working life.
the invention discloses hot-end component heat shield structure in a kind of gas turbine gas collection housing, comprise the sealing gland ring, snap ring, heat insulation cover plate, mounting flange, the compressorshaft of described gas turbine is to diffuser exit, the combustion gas volute, the exhaust section of turbine, the rotor casing all is arranged in the gas collection housing, be full of the pressurized air that described compressorshaft is discharged to diffuser exit in described gas collection housing, comprise firing chamber high-temperature fuel gas out in described combustion gas volute, the outlet of combustion gas volute links together with the nozzle ring import, it is characterized in that
Described sealing gland ring, snap ring, heat insulation cover plate, mounting flange are fixedly connected sequentially, described mounting flange and gas collection housing Bolt Connection, wherein,
Some rows radially pore vertically distributes on the peripheral wall of described heat insulation cover plate;
Some row's ring-type parietal tooths that distribute vertically on the inner peripheral wall of described sealing gland ring,
Described heat shield structure covers the turbine exhaust section parts outsides, forms the labyrinth air seal passage between described sealing gland ring and combustion gas volute installing ring, both between the long and narrow air film layer of formation; Formation sealing gland space between outside described heat insulation cover plate and turbine exhaust section parts, cool air in described gas collection housing enters described sealing gland space from described labyrinth air seal passage, and by described radially pore outflow sealing gland space, realize the received heat of cool air in the gas collection housing is controlled.
Preferably, the pore row of described radially pore, every exhaust port quantity, aperture are variable, and the circumferential angle of each exhaust port can be zero or non-zero.Hot air flowrate in described sealing gland space can be by quantity and the aperture adjustment of pore.There is circumferential angle in pore if each arranges radially, and the temperature field of heat insulation cover plate is heated evenly, and prevents unnecessary thermal distortion or fire damage, affects whole pneumatic circulating and heat transfer effect.
Preferably, described sealing gland ring is embedded in the snap ring inner ring, is fixed by the snap ring flanging side face.
Preferably, described snap ring and heat insulation cover plate are along circumference soldering.The two ends of snap ring are the connection flange.
Preferably, described heat insulation cover plate and mounting flange are along circumference soldering.
Preferably, the tubular flared section that described heat insulation cover plate comprises cylindrical body and is integrally formed therewith, described radially pore is formed on the peripheral wall of described cylindrical body.The two ends of heat insulation cover plate are welding edge.
Preferably, described mounting flange comprises bolt hole and welding edge, and described tubular flared section is along the circumference soldering of welding edge.
Working principle of the present invention: thermal shield and gas collection housing by Bolt Connection together, sealing gland ring and combustion gas volute installing ring form the labyrinth air seal passage, thermal shield covers the turbine exhaust section parts outsides, has long and narrow air film layer between both.Heat insulation cover plate is provided with radially pore of some rows, and pore row, every exhaust port quantity, aperture are variable, and the circumferential angle of each exhaust port can be zero or non-zero.In sealing gland, there is thermal gradient in the outer air of air and sealing gland, and then forms aerodynamic force, and radially orifice flow is to the sealing gland external space for air-flow, and at this moment, hot air flowrate can be by quantity and the aperture adjustment of pore.In the gas flow process, make static pressure in the sealing gland space lower than the static pressure outside the sealing gland space, thereby at the place, gap of sealing gland ring and combustion gas volute installing ring, cool air can flow to the sealing gland space, and continues to radially stomatal movement, finally flows out space in sealing gland.In process, cool air and hot air generation heat exchange make the hot air that flows out the sealing gland space that to a certain degree temperature drop be arranged, and have controlled the received heat of cool air in the gas collection housing.There is circumferential angle in pore if each arranges radially, and the temperature field of heat insulation cover plate is heated evenly, and prevents unnecessary thermal distortion or fire damage, affects whole pneumatic circulating and heat transfer effect.
Heat shield structure of the present invention is compared with prior art has following significant advantage:
The present invention is simple in structure, cost is low, be easy to processing, solar heat protection is effective, can effectively reduce combustion machine hot-end component to the superheating of gas collection housing compressed air, prevent that the shafting components ambient temperature is too high, cause the thermal failure fault, can guarantee stability, the reliability of working rotor, extend its working life.
Description of drawings
Fig. 1 is the scheme of installation of heat shield structure of the present invention in gas turbine;
Fig. 2 is the sectional drawing of thermal shield assembly of the present invention;
Fig. 3 (a) is sealing gland structure of rings figure, and Fig. 3 (b) is the partial enlarged drawing of sealing gland ring;
Fig. 4 is Snap ring structure figure;
Fig. 5 is the thermal shield composition that hardens;
Fig. 6 is heat insulation cover plate sectional view;
Fig. 7 is the mounting flange structural drawing;
Fig. 8 is the thin composition of mounting flange.
Embodiment
For the purpose, technological scheme and the advantage that make invention is clearer, referring to the accompanying drawing embodiment that develops simultaneously, the present invention is described in more detail.
as shown in Fig. 1 to 8, hot-end component heat shield structure 10 in gas turbine gas collection housing of the present invention, comprise sealing gland ring 1, snap ring 2, heat insulation cover plate 3, mounting flange 4, the compressorshaft of described gas turbine is to diffuser exit 12, combustion gas volute 6, the exhaust section of turbine 9, the rotor casing all is arranged in gas collection housing 7, be full of the pressurized air 5 that described compressorshaft is discharged to diffuser exit 12 in described gas collection housing 7, comprise firing chamber high-temperature fuel gas out in described combustion gas volute 6, 6 outlets of combustion gas volute link together with nozzle ring 8 imports, described sealing gland ring 1, snap ring 2, heat insulation cover plate 3, mounting flange 4 is fixedly connected sequentially, described mounting flange 4 and gas collection housing 7 Bolt Connection, wherein, some rows radially pore 302 vertically distributes on the peripheral wall of described heat insulation cover plate 3, some row's ring-type parietal tooths 101 vertically distribute on the inner peripheral wall of described sealing gland ring 1, described heat shield structure 10 covers the turbine 9 exhaust section parts outsides, forms the labyrinth air seal passage between described sealing gland ring 1 and combustion gas volute installing ring 11, both between the long and narrow air film layer of formation, formation sealing gland space between outside described heat insulation cover plate 3 and turbine 9 exhaust section parts, cool air in described gas collection housing 7 enters described sealing gland space from described labyrinth air seal passage, and flow out the sealing gland space by described radially pore 302, realize the received heat of gas collection housing 7 interior cool airs is controlled.
The pore row of described radially pore 302, every exhaust port quantity, aperture are variable, and the circumferential angle of each exhaust port can be zero or non-zero.Hot air flowrate in described sealing gland space can be by quantity and the aperture adjustment of pore.There is circumferential angle in pore 302 if each arranges radially, and the temperature field of heat insulation cover plate is heated evenly, and prevents unnecessary thermal distortion or fire damage, affects whole pneumatic circulating and heat transfer effect.
Working principle of the present invention: thermal shield 10 and gas collection housing 7 by Bolt Connection together, sealing gland ring 1 forms the labyrinth air seal passages with combustion gas volute installing ring 11, thermal shield 10 covers the turbine exhaust section parts outsides, has long and narrow air film layer between both.Heat insulation cover plate 3 is provided with radially pore 302 of some rows, and pore row, every exhaust port quantity, aperture are variable, and the circumferential angle of each exhaust port can be zero or non-zero.In sealing gland, there is thermal gradient in the outer air of air and sealing gland, and then forms aerodynamic force, and air-flow radially hole 302 flows to the sealing gland external space, and at this moment, hot air flowrate can be by quantity and the aperture adjustment of pore.In the gas flow process, make static pressure in the sealing gland space lower than the static pressure outside the sealing gland space, thereby at the place, gap of sealing gland ring and combustion gas volute installing ring, cool air can flow to the sealing gland space, and continues to radially stomatal movement, finally flows out space in sealing gland.In process, cool air and hot air generation heat exchange make the hot air that flows out the sealing gland space that to a certain degree temperature drop be arranged, and have controlled the received heat of cool air in the gas collection housing.There is circumferential angle in pore if each arranges radially, and the temperature field of heat insulation cover plate is heated evenly, and prevents unnecessary thermal distortion or fire damage, affects whole pneumatic circulating and heat transfer effect.
The above is only preferred embodiment of the present invention, and is in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of making, is equal to replacement, improvement etc., all should be included within the scope of the present invention.
Claims (8)
1. hot-end component heat shield structure in a gas turbine gas collection housing, comprise the sealing gland ring, snap ring, heat insulation cover plate, mounting flange, the compressorshaft of described gas turbine is to diffuser exit, the combustion gas volute, the exhaust section of turbine, the rotor casing all is arranged in the gas collection housing, be full of the pressurized air that described compressorshaft is discharged to diffuser exit in described gas collection housing, comprise firing chamber high-temperature fuel gas out in described combustion gas volute, the outlet of combustion gas volute links together with the nozzle ring import, it is characterized in that
Described sealing gland ring, snap ring, heat insulation cover plate, mounting flange are fixedly connected sequentially, described mounting flange and gas collection housing Bolt Connection, wherein,
Some rows radially pore vertically distributes on the peripheral wall of described heat insulation cover plate;
Some row's ring-type parietal tooths that distribute vertically on the inner peripheral wall of described sealing gland ring 1,
Described heat shield structure covers the turbine exhaust section parts outsides, forms the labyrinth air seal passage between described sealing gland ring and combustion gas volute installing ring, both between the long and narrow air film layer of formation; Formation sealing gland space between outside described heat insulation cover plate and turbine exhaust section parts, cool air in described gas collection housing enters described sealing gland space from described labyrinth air seal passage, and by described radially pore outflow sealing gland space, realize the received heat of cool air in the gas collection housing is controlled.
2. heat-insulating structure according to claim 1, it is characterized in that, the pore row of described radially pore, every exhaust port quantity, aperture are variable, and the circumferential angle of each exhaust port can be zero or non-zero, and the hot air flowrate in described sealing gland space can be passed through quantity and the aperture adjustment of pore.
3. heat-insulating structure according to claim 1 and 2, is characterized in that, each arranges radially that there is circumferential angle in pore.
4. heat-insulating structure according to claim 1, is characterized in that, described sealing gland ring is embedded in the snap ring inner ring, is fixed by the snap ring flanging side face.
5. according to the described heat-insulating structure of above-mentioned any one claim, it is characterized in that, described snap ring and heat insulation cover plate are along circumference soldering, and the two ends of described snap ring are the connection flange.
6. according to the described heat-insulating structure of above-mentioned any one claim, it is characterized in that, described heat insulation cover plate and mounting flange are along circumference soldering.
7. according to the described heat-insulating structure of above-mentioned any one claim, it is characterized in that, the tubular flared section that described heat insulation cover plate comprises cylindrical body and is integrally formed therewith, described radially pore is formed on the peripheral wall of described cylindrical body, and the two ends of described heat insulation cover plate are welding edge.
8. according to the described heat-insulating structure of above-mentioned any one claim, it is characterized in that, described mounting flange comprises bolt hole and welding edge, and described tubular flared section is along the circumference soldering of welding edge.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310020446.6A CN103089451B (en) | 2013-01-18 | 2013-01-18 | Thermal-protection cover |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310020446.6A CN103089451B (en) | 2013-01-18 | 2013-01-18 | Thermal-protection cover |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN103089451A true CN103089451A (en) | 2013-05-08 |
| CN103089451B CN103089451B (en) | 2015-01-28 |
Family
ID=48202476
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310020446.6A Expired - Fee Related CN103089451B (en) | 2013-01-18 | 2013-01-18 | Thermal-protection cover |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103089451B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109578141A (en) * | 2019-01-23 | 2019-04-05 | 中国船舶重工集团公司第七0三研究所 | It is a kind of can astern gas turbine power turbine exhaust volute |
| CN113586252A (en) * | 2021-08-10 | 2021-11-02 | 江苏科技大学 | Gas turbine box package environment control system and control method thereof |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4166878A (en) * | 1976-10-01 | 1979-09-04 | Caterpillar Tractor Co. | Gas turbine engine internal insulation comprising metallic mesh--restrained ceramic fiber layer |
| CN2092608U (en) * | 1990-12-14 | 1992-01-08 | 北京市西城区新开通用试验厂 | Power devices with multi-energy output for gas turbine |
| CN1127327A (en) * | 1994-10-01 | 1996-07-24 | Abb管理有限公司 | Method and apparatus for sealing and cooling gas discharging side axle of axial gas turbine |
| US20050091984A1 (en) * | 2003-11-03 | 2005-05-05 | Robert Czachor | Heat shield for gas turbine engine |
| CN101118052A (en) * | 2007-09-25 | 2008-02-06 | 王其林 | LED lamp heat radiation method applying cross-ventilation warehouse |
| CN102094712A (en) * | 2009-12-09 | 2011-06-15 | 北京融润耦合动力技术研究院 | Micro gas turbine system with gas bearing-rotor structure |
-
2013
- 2013-01-18 CN CN201310020446.6A patent/CN103089451B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US4166878A (en) * | 1976-10-01 | 1979-09-04 | Caterpillar Tractor Co. | Gas turbine engine internal insulation comprising metallic mesh--restrained ceramic fiber layer |
| CN2092608U (en) * | 1990-12-14 | 1992-01-08 | 北京市西城区新开通用试验厂 | Power devices with multi-energy output for gas turbine |
| CN1127327A (en) * | 1994-10-01 | 1996-07-24 | Abb管理有限公司 | Method and apparatus for sealing and cooling gas discharging side axle of axial gas turbine |
| US20050091984A1 (en) * | 2003-11-03 | 2005-05-05 | Robert Czachor | Heat shield for gas turbine engine |
| CN101118052A (en) * | 2007-09-25 | 2008-02-06 | 王其林 | LED lamp heat radiation method applying cross-ventilation warehouse |
| CN102094712A (en) * | 2009-12-09 | 2011-06-15 | 北京融润耦合动力技术研究院 | Micro gas turbine system with gas bearing-rotor structure |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109578141A (en) * | 2019-01-23 | 2019-04-05 | 中国船舶重工集团公司第七0三研究所 | It is a kind of can astern gas turbine power turbine exhaust volute |
| CN109578141B (en) * | 2019-01-23 | 2023-10-20 | 中国船舶重工集团公司第七0三研究所 | Exhaust volute of reversing gas turbine power turbine |
| CN113586252A (en) * | 2021-08-10 | 2021-11-02 | 江苏科技大学 | Gas turbine box package environment control system and control method thereof |
Also Published As
| Publication number | Publication date |
|---|---|
| CN103089451B (en) | 2015-01-28 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CA2879376C (en) | Active clearance control system | |
| US9376961B2 (en) | System for controlling a flow rate of a compressed working fluid to a combustor fuel injector | |
| US9115585B2 (en) | Seal assembly for gas turbine | |
| EP2902605B1 (en) | A fuel manifold and fuel injector arrangement for a gas turbine engine | |
| RU2558731C2 (en) | Mounting structure of nozzle guide vanes at inlet channel of radial gas turbine of engine | |
| CN104061596A (en) | Flow Sleeve Assembly For A Combustion Module Of A Gas Turbine Combustor | |
| US20110081237A1 (en) | Sealing for vane segments | |
| US8701415B2 (en) | Flexible metallic seal for transition duct in turbine system | |
| JP6305441B2 (en) | Turbine engine | |
| JP6602094B2 (en) | Combustor cap assembly | |
| US9803555B2 (en) | Fuel delivery system with moveably attached fuel tube | |
| EP2565400B1 (en) | Exhaust gas duct for a gas turbine with heat resistant liner and gas turbine having such a gas duct | |
| CN103512046A (en) | Transition duct for a gas turbine | |
| CN103061889B (en) | Thermal insulating structure | |
| RU122447U1 (en) | GTD-25STA GAS-TURBINE ENGINE, COMPRESSOR, COMBUSTION CHAMBER, GAS-GENERATOR TURBINE, FREE TURBINE | |
| CN103089451B (en) | Thermal-protection cover | |
| CN203098055U (en) | Heat-insulating cover | |
| JP5756886B2 (en) | Steam turbine with thrust balance piston | |
| CN106731918B (en) | Sectional combined mixing chamber | |
| WO2016162239A1 (en) | Annular combustor for a gas turbine engine | |
| JP2018071543A (en) | Advanced seals with reduced corner leakage | |
| KR102622316B1 (en) | Integrated fuel nozzle connection | |
| CN106133293A (en) | Gas turbine | |
| RU2310086C1 (en) | Gas-turbine plant | |
| CN107701247A (en) | A kind of gas turbine guider inner ring impinging cooling structure, gas turbine |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20150128 |