CN202970913U - Supporting system of gas turbine - Google Patents
Supporting system of gas turbine Download PDFInfo
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- CN202970913U CN202970913U CN2012206407287U CN201220640728U CN202970913U CN 202970913 U CN202970913 U CN 202970913U CN 2012206407287 U CN2012206407287 U CN 2012206407287U CN 201220640728 U CN201220640728 U CN 201220640728U CN 202970913 U CN202970913 U CN 202970913U
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- turbine
- rotating shaft
- supporting
- underarm
- gas turbine
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Abstract
The utility model discloses a supporting system of a gas turbine, which belongs to the structural design of a gas turbine. The supporting system comprises a compressor cylinder supporting mechanism, a turbine cylinder supporting mechanism, an exhaust cylinder guide rail mechanism and a base, wherein the turbine cylinder supporting mechanism is composed of a supporting arm, a supporting arm rotor shaft, a lower supporting arm, a lower arm rotor shaft and a shaft base; and the supporting arm and the lower supporting arm can rotate around the supporting arm rotor shaft, and the lower supporting arm can rotate around the lower arm rotor shaft. The supporting system provided by the utility model adopts a structure that the lower supporting arm rotates around the lower arm rotor shaft in the turbine cylinder supporting mechanism, so that radial expansion generated by heating of a turbine cylinder can be compensated so as to avoid crackles of the supporting arm caused by the fact the turbine cylinder is heated to expand, the service life and the reliability of the supporting system are prolonged and improved, and the gas turbine can work stably and reliably.
Description
Technical field
The utility model relates to the gas turbine support system, belongs to the gas turbine structure design field.
Background technique
In industry gas turbine, support system commonly used is comprised of gas compressor cylinder supporting mechanism, turbine cylinder supporting mechanism, exhaust casing guide rail mechanism and base.General gas turbine blower cylinder supporting mechanism is positioned at gas compressor cylinder place, for fixed supporting mechanism is place, the absolute dead point of gas turbine; Turbine cylinder supporting mechanism is the on-fixed supporting mechanism, is positioned at turbine cylinder place, and the exhaust casing guide rail mechanism is positioned at the exhaust casing place.
In gas turbine when work,, air flows through the firing chamber after the gas compressor compression, in the firing chamber with combustion gas mixing after temperature raise, then through the turbine expansion acting, entered at last the equipment such as atmosphere or exhaust heat boiler by vent systems.During the gas turbine normal operation, the gas turbine body temperature raises gradually, cause the axial direction heated elongation of gas turbine body, gas compressor cylinder supporting mechanism is the absolute dead point of gas turbine axial elongation, therefore the gas turbine body from absolute dead point backward axial direction heated elongation become gradually large, because turbine cylinder temperature is higher, expanded by heating radially when making the axial direction heated elongation of turbine cylinder, and gas turbine turbine supporting mechanism is positioned at turbine cylinder place, so turbine cylinder supporting mechanism will guarantee supporting ﹠ stablizing, reliable operation in the gas turbine operation process.When guaranteeing gas turbine work by the exhaust casing guide rail mechanism more simultaneously, gas turbine is heated and extends vertically, does not deflect.
Traditional industry gas turbine support system generally is comprised of gas compressor cylinder supporting mechanism, turbine cylinder supporting mechanism, exhaust casing guide rail mechanism and base.It is absolute dead point that gas compressor cylinder supporting mechanism is fixed on base, the exhaust casing guide rail mechanism is positioned at the exhaust casing bottom, turbine cylinder supporting mechanism generally is made of support arm, support arm rotating shaft and axle bed, support arm is made by Plate Steel, left and right directions is fixed, by the radial expansion of being heated of Plate Steel elastic compensating gas turbine turbine cylinder.But support arm left and right resiliently deformable repeatedly easily causes between support arm and axle bed stress to concentrate to crack, reduce working life and the reliability of support system.Particularly on the gas turbine for frequent start and stop, this problem seems even more serious.
The model utility content
The purpose of this utility model is to provide a kind of gas turbine support system, thereby concentrate to avoid in turbine cylinder supporting mechanism between support arm and axle bed stress the phenomenon that cracks, the problem that the support system reliability that causes because of expanded by heating when solving industry gas turbine work and working life reduce improves the stability of gas turbine work.
The technical solution of the utility model is as follows:
A kind of gas turbine support system, contain gas compressor cylinder supporting mechanism, turbine cylinder supporting mechanism, exhaust casing guide rail mechanism and base, it is characterized in that: described turbine cylinder supporting mechanism comprises the rotating shaft of turbine cylinder lug, support arm, support arm rotating shaft, supports underarm, underarm rotating shaft and axle bed; The rotating shaft of turbine cylinder lug is arranged on the turbine cylinder of gas turbine, and the upper end of described support arm is connected with the rotating shaft of turbine cylinder lug, the support arm lower end by the support arm rotating shaft with support the underarm upper end and be connected, support arm and support underarm rotate around the support arm rotating shaft; Support the underarm lower end and be connected with axle bed on being arranged on base by the underarm rotating shaft, the support underarm rotates around the underarm rotating shaft.
The utility model compared with prior art, have the following advantages and the high-lighting effect: adopt in turbine cylinder supporting mechanism and support the structure that underarm rotates around the underarm rotating shaft, this structure can compensate by the turbine cylinder and be subjected to thermogenetic radial expansion volume, avoid producing the support arm crackle because of turbine cylinder expanded by heating, improved working life and the reliability of support system, guaranteed that gas turbine reliablely and stablely works.
Description of drawings
Fig. 1 is existing gas turbine support system schematic diagram.
Fig. 2 is the gas turbine support system schematic diagram that the utility model provides.
Fig. 3 is the structural representation of turbine cylinder supporting mechanism.
Fig. 4 is the work working principle schematic diagram of turbine cylinder supporting mechanism.
Fig. 5 is the A-A sectional view of Fig. 4.
List of parts: 10-gas compressor cylinder; 11-turbine cylinder; The 12-exhaust casing; 13-gas compressor cylinder supporting mechanism; 14-turbine cylinder supporting mechanism; 15-exhaust casing guide rail mechanism; The rotating shaft of 16-turbine cylinder lug; The 17-support arm; The rotating shaft of 18-support arm; 19-supports underarm; The rotating shaft of 20-underarm; The 21-axle bed; The 22-base.
Embodiment
Below in conjunction with accompanying drawing, structure of the present utility model, principle and working procedure are described further.
Fig. 1 is existing gas turbine overall structure schematic diagram, comprises gas turbine body and support system two-part, and the gas turbine body comprises gas compressor cylinder 10, turbine cylinder 11 and exhaust casing 12 from front to back successively; Support system comprises gas compressor cylinder supporting mechanism 13, turbine cylinder supporting mechanism 14, exhaust casing guide rail mechanism 15 and base 22; Gas compressor cylinder supporting mechanism 13 is connected with base with gas compressor cylinder 10 respectively, and turbine cylinder supporting mechanism 14 turbine cylinder 11 respectively is connected with base 22, and exhaust casing guide rail mechanism 15 is connected with base with exhaust casing 12 respectively.Gas compressor cylinder supporting mechanism 13 is fixed on base 22, be the axially absolute dead point of gas turbine, exhaust casing guide rail mechanism 15 does not deflect when guaranteeing gas turbines work, and the turbine cylinder supporting mechanism 14 secure support gas turbine after axial elongation and radial expansion that is heated when guaranteeing gas turbines work.
Fig. 2 is the gas turbine support system schematic diagram that the utility model provides.Wherein turbine cylinder supporting mechanism 14 is comprised of turbine cylinder lug rotating shaft 16, support arm 17, support arm rotating shaft 18, support underarm 19, underarm rotating shaft 20 and axle bed 21.Turbine cylinder lug rotating shaft 16 is arranged on the turbine cylinder 11 of gas turbine, the upper end of described support arm 17 is connected with turbine cylinder lug rotating shaft 16, support arm 17 lower ends by support arm rotating shaft 18 with support underarm 19 upper ends and be connected, support underarm 19 lower ends are connected with axle bed 21 on being arranged on base 22 by underarm rotating shaft 20.Support arm 17 and support underarm 19 can rotate around support arm rotating shaft 18; Supporting underarm 19 can rotate around underarm rotating shaft 20.
Fig. 3, Fig. 4 and Fig. 5 are gas turbine support system turbine cylinder supporting mechanism working principle schematic diagram of the present utility model, and support arm 17 upper ends are connected with turbine cylinder lug rotating shaft 16 on being arranged on turbine cylinder 11, can turn an angle around turbine cylinder lug rotating shaft 16.Support arm 17 lower ends are connected with support underarm 19 by support arm rotating shaft 18.The gas turbine work elongation backward of being heated axially, because support arm 17 can turn an angle around support arm rotating shaft 18, length and rotation angle by rational design support arm 17 can compensate the axial direction heated elongation backward of gas turbine (as shown in Figure 3).Support underarm 19 upper ends and be connected with support arm rotating shaft 18, support underarm 19 lower ends are connected with axle bed 21 on being fixed on base 22 by underarm rotating shaft 20.Gas turbine work turbine cylinder 11 radial expansions of being heated, can turn an angle around underarm rotating shaft 20 owing to supporting underarm 19, the length and the rotation angle that support underarm 19 by rational design can compensate gas turbine turbine cylinder 11 radial expansion volumes (as shown in Figure 4).
Claims (1)
1. gas turbine support system, contain gas compressor cylinder supporting mechanism (13), turbine cylinder supporting mechanism (14), exhaust casing guide rail mechanism (15) and base (22), it is characterized in that: described turbine cylinder supporting mechanism (14) comprises turbine cylinder lug rotating shaft (16), support arm (17), support arm rotating shaft (18), supports underarm (19), underarm rotating shaft (20) and axle bed (21); Turbine cylinder lug rotating shaft (16) is arranged on the turbine cylinder (11) of gas turbine, the upper end of described support arm (17) is connected with turbine cylinder lug rotating shaft (16), support arm (17) lower end by support arm rotating shaft (18) with support underarm (19) upper end and be connected, support arm (17) and support underarm (19) rotate around support arm rotating shaft (18); Support underarm (19) lower end and be connected with axle bed (21) on being arranged on base (22) by underarm rotating shaft (20), support underarm (19) rotates around underarm rotating shaft (20).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012206407287U CN202970913U (en) | 2012-11-28 | 2012-11-28 | Supporting system of gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2012206407287U CN202970913U (en) | 2012-11-28 | 2012-11-28 | Supporting system of gas turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN202970913U true CN202970913U (en) | 2013-06-05 |
Family
ID=48511998
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2012206407287U Expired - Lifetime CN202970913U (en) | 2012-11-28 | 2012-11-28 | Supporting system of gas turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN202970913U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102926873A (en) * | 2012-11-28 | 2013-02-13 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine support system |
-
2012
- 2012-11-28 CN CN2012206407287U patent/CN202970913U/en not_active Expired - Lifetime
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102926873A (en) * | 2012-11-28 | 2013-02-13 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | Gas turbine support system |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| PE01 | Entry into force of the registration of the contract for pledge of patent right |
Denomination of utility model: Gas turbine support system Effective date of registration: 20161104 Granted publication date: 20130605 Pledgee: Tsinghua Holdings Co.,Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. Registration number: 2016990000853 |
|
| PLDC | Enforcement, change and cancellation of contracts on pledge of patent right or utility model | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right | ||
| PC01 | Cancellation of the registration of the contract for pledge of patent right |
Date of cancellation: 20191211 Granted publication date: 20130605 Pledgee: Tsinghua Holdings Co.,Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. Registration number: 2016990000853 |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20191223 Address after: 102209 Beijing Changping District in the future of the national electric investment group Park in the future science city south of Beijing Patentee after: CHINA UNITED HEAVY GAS TURBINE TECHNOLOGY Co.,Ltd. Address before: 100084 No. 8, building 1, No. 1001, Zhongguancun East Road, Beijing, Haidian District Patentee before: Beijing Huatsing Gas Turbine & IGCC Technology Co.,Ltd. |
|
| CX01 | Expiry of patent term | ||
| CX01 | Expiry of patent term |
Granted publication date: 20130605 |