CN104265382A - Exhaust system of gas turbine - Google Patents
Exhaust system of gas turbine Download PDFInfo
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- CN104265382A CN104265382A CN201410500334.5A CN201410500334A CN104265382A CN 104265382 A CN104265382 A CN 104265382A CN 201410500334 A CN201410500334 A CN 201410500334A CN 104265382 A CN104265382 A CN 104265382A
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Abstract
The invention discloses an exhaust system of a gas turbine. The exhaust system comprises a shell, a sealing member, connecting pieces, a support, a pedestal, a heat dissipation layer, an isolating layer, a pad and a pressing plate, wherein the shell is of a transverse cylindrical steel plate structure with a big end and a small end and is assembled and connected by the connecting pieces; the sealing member is arranged on the inner edge of an inlet in the small end of the shell; the upper end of the support is connected below the transverse shell, and the lower end of the support is connected with the pedestal; the heat dissipation layer is tightly attached to the inner wall of the shell; the isolating layer is connected with the heat dissipation layer and is laid along the side wall; the pad is arranged on the other side of the isolating layer and is fixedly connected through the pressing plate by using bolts and nuts. According to the product, the heat efficiency can be integrally improved, the thermal stress produced by non-uniform heating on a heated surface is relieved, stress concentration is avoided, and the safety of operation is improved; meanwhile, the failure condition in operation of the conventional products can also be eliminated, and the product cost is reduced and the development period is shortened on the premise of guaranteeing the product quality.
Description
Technical field
The invention belongs to gas turbine technology field, relate to a kind of combustion turbine exhaustion system.
Background technique
Due to China's rapid development of economy, the demand of electric power energy is constantly increased, but day by day serious along with global warming problem, and mineral resources is increasingly poor, the demand of various clean energy resource just seems particularly important.
Gas Turbine Combined-cycle (GTCC), also known as combustion gas-Steam Combined Cycle, refer to a kind of generation mode gas turbine and steam turbine combined, form primarily of gas turbine (gas compressor, firing chamber, turbine, control system and auxiliary system), exhaust heat boiler, steam turbine three part.Gas compressor is sent in firing chamber after sucking air compressing, fuel (oil or rock gas) burning is made to produce high-temperature high-pressure fuel gas, enter the generating of gas turbine expansion work, again the gas that gas turbine is discharged is introduced boiler (exhaust heat boiler), as the thermal source of boiler, the steam utilizing boiler to produce enters steam turbine and generates electricity.Material is thus formed gas turbine and steam turbine jointly as the association circulating power generation system of prime mover, have general thermal power plant the high thermal efficiency that is beyond one's reach, as a kind of novel electric power energy device, there is wide market development space.
Vent systems is the important auxiliary system of gas turbine, has a significant impact its efficiency and normal work.Its major function maintains exhaust pressure thus guarantees combustion engine efficiency, airtight combustion gas directing exhaust gas trend.If exhaust system structure design is unreasonable; there is resonance or lost efficacy due to insufficient strength; vent systems will be caused to produce Large travel range, and gas turbine combustion gas can not unobstructed discharge and affect gas turbine and normally work, thus reduces gas turbine proficiency and even cause gas turbine to be shut down.Equally, if thermal design is unreasonable, the overheated even gas leakage of vent systems housing will be produced, thus harm personal safety, and cause gas turbine to be shut down.Due to the particularity of power industry; the shutdown outside the plan of gas turbine not only can have an impact to the economic benefit of power plant self; also can produce electrical network and impact; particularly in China; gas turbine is many carries out peaking operation in peak of power consumption month or period; shutdown now probably causes regional power failure, and then affects production and the life of people.
Summary of the invention
Technical problem to be solved by this invention is, overcomes the shortcoming of prior art, provides a kind of combustion turbine exhaustion system, this product not only overallly can improve the thermal efficiency, alleviate heating surface to be heated the thermal stress of uneven generation, avoid stress to concentrate, improve the Security run; The failure conditions of product emerged in operation in the past can also be eliminated simultaneously, and under the prerequisite ensureing quality of product, reduce product cost, shorten the lead time.
In order to solve above technical problem, the invention provides a kind of combustion turbine exhaustion system, comprise housing, Sealing, link, support and base, housing is the little cylinder-shaped steel plate structure in horizontal large one end, one end, and be made up of link assembly and connection, the little end entrance that Sealing is located at housing is interior along place, support the below that upper end connects horizontal housing, and support lower end connection base, also comprise heat dissipating layer, separation layer, liner and pressing plate, heat dissipating layer is close to inner walls and is arranged, separation layer connects heat dissipating layer and lays along sidewall, separation layer opposite side arranges liner, liner adopts screw bolt and nut to be connected and fixed by pressing plate.
Link comprises flange, screw bolt and nut, and flange is welded on the splice jointing of two pieces of housings respectively, then two flange screw bolt and nut alignment is connected and fixed.
Main alloy element Cr in the alloyed steel that middle shell of the present invention adopts and Mo significantly improves the hardening capacity of steel, and these alloying elements have postponed the transformation in cooling procedure, improves the stability of undercooled austenite.
The technological scheme that the present invention limits further is:
Aforementioned seal part is flexible seals, is the one of rubber, pottery, rubber-asbestos slate or aerogel blanket-polyurethane; Heat dissipating layer is the one of ceramic fiber layer, glass fibre layer or carbon fiber layer; Separation layer is glass fibre layer or boron fiber layer; Liner is the one of graphite layer or ceramic fiber layer, and liner is uniformly distributed radiation hole, and the diameter of described radiation hole is 0.4-1.6mm.
The invention has the beneficial effects as follows:
The heat dissipating layer of product of the present invention, separation layer and liner, all can use ceramic fiber, and ceramic fiber has the features such as lightweight, high temperature resistant, good thermal stability, heat conductivity are low, specific heat is little, mechanical resistant vibrations, high-temperature heat insulation are functional, avirulent.
The liner of product of the present invention adopts graphite, has thermally-stabilised, selflubricating, corrosion-resistant, not aging, the not feature such as embrittlement, in the use that the working condition of harshness can be steady in a long-term, seldom needs to safeguard; There is good anticorrosive property, high-and low-temperature resistance simultaneously, good compression resilience and high strength.
This product protection temperatures as high 620 degree, can renitency value be 850-12500Pa, throughput be 1695m
3/ s, not only overall can improve the thermal efficiency, alleviates heating surface and to be heated the thermal stress of uneven generation, avoid stress to concentrate, improve the Security run; The failure conditions of product emerged in operation in the past can also be eliminated simultaneously, and under the prerequisite ensureing quality of product, reduce product cost, shorten the lead time.
Accompanying drawing explanation
Fig. 1 is sectional view of the present invention;
Wherein, 1-housing, 2-Sealing, 3-heat dissipating layer, 4-separation layer, 5-liner, 6-pressing plate, 7-link, 8-supports, 9-base.
Embodiment
embodiment 1
The present embodiment provides a kind of combustion turbine exhaustion system, structure as shown in Figure 1, comprise housing 1, Sealing 2, link 7, support 8 and base 9, housing 1 is the little cylinder-shaped steel plate structure in horizontal large one end, one end, and be made up of link 7 assembly and connection, the little end entrance that Sealing 2 is located at housing 1 is interior along place, support the below that 8 upper ends connect horizontal housing 1, and support 8 lower ends connection bases 9, also comprise heat dissipating layer 3, separation layer 4, liner 5 and pressing plate 6, heat dissipating layer 3 is close to housing 1 inwall and is arranged, separation layer 4 connects heat dissipating layer 3 and lays along sidewall, separation layer 4 opposite side arranges liner 5, liner 5 adopts screw bolt and nut to be connected and fixed by pressing plate 6.
Former connector 7 comprises flange, screw bolt and nut, and flange is welded on the splice jointing of two pieces of housings 1 respectively, then two flange screw bolt and nut alignment is connected and fixed; Sealing 2 is flexible seals, for rubber material is made; Heat dissipating layer 3 is ceramic fiber layer; Separation layer 4 is glass fibre layer; Liner 5 is graphite layer, and liner 5 is uniformly distributed radiation hole, and the diameter of radiation hole is 0.8mm.
During this product work, gas flow is through this combustion turbine exhaustion system, the heat that combustion gas is carried passes to liner 5 by convection heat exchange, then the separation layer 4 of next-door neighbour is passed to from liner 5, heat dissipating layer 3 is passed to again from separation layer 4, finally transfer heat to housing 1, be then delivered in physical environment by the outer surface of housing 1 and the convection current of air and radiation heat transfer and go.
Above embodiment is only and technological thought of the present invention is described, can not limit protection scope of the present invention with this, and every technological thought proposed according to the present invention, any change that technological scheme basis is done, all falls within scope.
Claims (6)
1. a combustion turbine exhaustion system, comprise housing (1), Sealing (2), link (7), support (8) and base (9), described housing (1) is the little cylinder-shaped steel plate structure in large one end, horizontal one end, and be made up of link (7) assembly and connection, the little end entrance that described Sealing (2) is located at described housing (1) is interior along place, described support (8) upper end connects the below of described horizontal housing (1), and described support (8) lower end connects described base (9), it is characterized in that, also comprise heat dissipating layer (3), separation layer (4), liner (5) and pressing plate (6), described heat dissipating layer (3) is close to described housing (1) inwall and is arranged, described separation layer (4) connects described heat dissipating layer (3) and lays along sidewall, described separation layer (4) opposite side arranges described liner (5), described liner (5) adopts screw bolt and nut to be connected and fixed by pressing plate (6).
2. combustion turbine exhaustion system according to claim 1, it is characterized in that, described link (7) comprises flange, screw bolt and nut, and described flange is welded on the splice jointing of two pieces of housings (1) respectively, then two flange screw bolt and nut alignment is connected and fixed.
3. combustion turbine exhaustion system according to claim 1, is characterized in that, described Sealing (2) is flexible seals, for rubber, pottery, rubber-asbestos slate or aerogel blanket-polyurethane a kind of makes.
4. combustion turbine exhaustion system according to claim 1, is characterized in that, described heat dissipating layer (3) is ceramic fiber layer, the one of glass fibre layer or carbon fiber layer.
5. combustion turbine exhaustion system according to claim 1, is characterized in that, described separation layer (4) is glass fibre layer or boron fiber layer.
6. combustion turbine exhaustion system according to claim 1, is characterized in that, the one that described liner (5) is graphite layer or ceramic fiber layer, and described liner (5) is uniformly distributed radiation hole, and the diameter of described radiation hole is 0.4-1.6mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410500334.5A CN104265382B (en) | 2014-09-25 | 2014-09-25 | A kind of combustion turbine exhaustion system |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410500334.5A CN104265382B (en) | 2014-09-25 | 2014-09-25 | A kind of combustion turbine exhaustion system |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN104265382A true CN104265382A (en) | 2015-01-07 |
| CN104265382B CN104265382B (en) | 2015-12-02 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410500334.5A Active CN104265382B (en) | 2014-09-25 | 2014-09-25 | A kind of combustion turbine exhaustion system |
Country Status (1)
| Country | Link |
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| CN (1) | CN104265382B (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107524524A (en) * | 2017-10-24 | 2017-12-29 | 江苏华强新能源科技有限公司 | A kind of high-efficiency gas turbine gas extraction system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0791726A1 (en) * | 1996-02-21 | 1997-08-27 | Braden Manufacturing | Exhaust gas diffuser interface |
| CN1215795A (en) * | 1997-09-25 | 1999-05-05 | 三菱重工业株式会社 | Gas turbine exhaust passage and damper system for same |
| US6807803B2 (en) * | 2002-12-06 | 2004-10-26 | General Electric Company | Gas turbine exhaust diffuser |
| CN103527266A (en) * | 2012-06-28 | 2014-01-22 | 阿尔斯通技术有限公司 | Diffuser for the exhaust section of a gas turbine and gas turbine |
| CN204098970U (en) * | 2014-09-25 | 2015-01-14 | 江苏华强新能源科技有限公司 | Combustion turbine exhaustion system |
-
2014
- 2014-09-25 CN CN201410500334.5A patent/CN104265382B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP0791726A1 (en) * | 1996-02-21 | 1997-08-27 | Braden Manufacturing | Exhaust gas diffuser interface |
| CN1215795A (en) * | 1997-09-25 | 1999-05-05 | 三菱重工业株式会社 | Gas turbine exhaust passage and damper system for same |
| US6807803B2 (en) * | 2002-12-06 | 2004-10-26 | General Electric Company | Gas turbine exhaust diffuser |
| CN103527266A (en) * | 2012-06-28 | 2014-01-22 | 阿尔斯通技术有限公司 | Diffuser for the exhaust section of a gas turbine and gas turbine |
| CN204098970U (en) * | 2014-09-25 | 2015-01-14 | 江苏华强新能源科技有限公司 | Combustion turbine exhaustion system |
Non-Patent Citations (2)
| Title |
|---|
| 孙磊: "《9F燃气轮机排气系统结构设计及分析》", 《中国优秀硕士学位论文全文数据库 工程科技II辑（月刊）》 * |
| 郑海英 等: "《燃气轮机排气扩散器的设计特点》", 《锅炉技术》 * |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107524524A (en) * | 2017-10-24 | 2017-12-29 | 江苏华强新能源科技有限公司 | A kind of high-efficiency gas turbine gas extraction system |
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| Publication number | Publication date |
|---|---|
| CN104265382B (en) | 2015-12-02 |
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