CN204591376U - A kind of gas turbine combustion cylinder pressure heat-insulating structure - Google Patents
A kind of gas turbine combustion cylinder pressure heat-insulating structure Download PDFInfo
- Publication number
- CN204591376U CN204591376U CN201520069507.2U CN201520069507U CN204591376U CN 204591376 U CN204591376 U CN 204591376U CN 201520069507 U CN201520069507 U CN 201520069507U CN 204591376 U CN204591376 U CN 204591376U
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- China
- Prior art keywords
- cylinder pressure
- insulating tube
- heat insulating
- combustion cylinder
- gas turbine
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Abstract
The utility model relates to gas turbine field, disclose a kind of gas turbine combustion cylinder pressure heat-insulating structure, described combustion cylinder pressure comprises outer shell and inner casing, described inner casing and outer shell form the chamber of combustion cylinder pressure jointly, the multiple bearings connecting outer shell and inner casing are provided with in described chamber, the bleed hole being communicated with described outer shell and inner casing is provided with in bearing described at least one, heat insulating tube is provided with in described bleed hole, the inlet end of described heat insulating tube and the suction port in described bleed hole are connected, and leave gap between the pipe shaft of described heat insulating tube and described bleed hole.The heat exchange that the utility model effectively can be isolated the cold air in bleed hole and be fired between cylinder pressure chamber, avoids the generation of thermal stress; And can avoid producing excessive thermal stress between heat insulating tube and bearing.
Description
Technical field
The utility model relates to gas turbine technology field, particularly relates to a kind of gas turbine combustion cylinder pressure heat-insulating structure.
Background technique
The continuous innovation of modern gas turbines technology and development, for improving the overall thermal efficiency of combustion engine, turbine inlet temperature constantly raises.Turbine rotor blade works under high temperature environment as high-speed rotary part simultaneously, and only rely on the raising of materials'use temperature cannot meet actual user demand, turbine rotor blade must take the cooling of certain forms.Turbine rotor blade, cooling air generally bleed from gas compressor, along with cooling require more and more higher, rate of air sucked in required demand is also increasing, will cause the decline of thermal efficiency of gas turbine.
Therefore a kind of ideal method is, from the air that gas compressor 1 is extracted out, through interstage cooler 4, the temperature that gas compressor 1 is bled is reduced further, to reduce the flow of bleeding, increases the efficiency of cycle of complete machine.But adopt this scheme to cool, an inevitable problem is exactly, and how to be bled by cooled gas compressor 1, is reintroduced back to internal rotor, so that cooling turbine movable vane 7.Combustion cylinder pressure inner casing 9, outer shell 8 as shown in Figure 1, are designed to integrative-structure by existing scheme, adopt several bearings 10 to connect, be processed with vent 11 in bearing 10 between inside and outside cylinder, and cooling air enters rotor 13 inside by vent 11 and cools.
Because the air in vent 11 is after the cooling of supercooler 4, temperature reduces greatly, for bearing 10, inside is connected with the cooling air of low temperature, outside then by combustion cylinder pressure 3 chamber 5 in high-temperature gas surround, to cause bearing 10 thermal stress greatly, excessive thermal stress can cause bearing 10 to crack and damage.
Model utility content
(1) technical problem that will solve
First technical problem to be solved in the utility model is the cold air of how effectively to isolate in bleed hole and the heat exchange of firing between cylinder pressure chamber, avoids the generation of thermal stress;
The second technical problem solved how to avoid producing excessive thermal stress between heat insulating tube and bearing.
(2) technological scheme
In order to solve the problems of the technologies described above, the utility model provides a kind of gas turbine to fire cylinder pressure heat-insulating structure, described combustion cylinder pressure comprises outer shell and inner casing, described inner casing and outer shell form the chamber of combustion cylinder pressure jointly, the multiple bearings connecting outer shell and inner casing are provided with in described chamber, the bleed hole being communicated with described outer shell and inner casing is provided with in bearing described at least one, heat insulating tube is provided with in described bleed hole, the inlet end of described heat insulating tube and the suction port in described bleed hole are connected, and leave gap between the pipe shaft of described heat insulating tube and described bleed hole.
Wherein, the inlet end of described heat insulating tube is provided with annular boss, and the inlet end of described heat insulating tube is connected by the suction port in described annular boss and described bleed hole.
Wherein, the top of the inlet end of described heat insulating tube is provided with flange.
Wherein, described combustion cylinder pressure is provided with breathing pipe and cooler, and the two ends of described cooler are communicated with described outer shell by described breathing pipe, and the outlet side of described breathing pipe and the inlet end of described heat insulating tube pass through Flange joint.
Wherein, the pipe shaft of described heat insulating tube is interval with one or more described annular boss along its length.
Wherein, the outer surface of the one or more described annular boss be positioned on described heat insulating tube pipe shaft is circular arc.
Preferably, the outer surface of described heat insulating tube is enclosed with thermal-protective material.
Wherein, described heat insulating tube is that stainless steel is made.
(3) beneficial effect
Compared with prior art, the utility model has the following advantages:
A kind of gas turbine combustion cylinder pressure heat-insulating structure that the utility model provides, adopts and be provided with heat insulating tube in bleed hole, the heat exchange effectively can isolated the cold air in bleed hole and fire between cylinder pressure chamber, thus avoid the generation of thermal stress; And adopt the suction port in the inlet end of described heat insulating tube and described bleed hole to be connected, gap is left between the pipe shaft of described heat insulating tube and described bleed hole, thus make heat insulating tube can free deformation, and then avoid producing excessive thermal stress between described heat insulating tube and bearing.
Accompanying drawing explanation
Fig. 1 is the overall structure schematic diagram of prior art combustion cylinder pressure;
Fig. 2 is the overall structure schematic diagram of a kind of gas turbine combustion of the utility model cylinder pressure heat-insulating structure;
Fig. 3 is the heat insulating tube structure of the utility model embodiment one;
Fig. 4 is the heat insulating tube structure of the utility model embodiment two;
Fig. 5 is the heat insulating tube structure of the utility model embodiment three.
In figure: 1: gas compressor; 2: firing chamber; 3: combustion cylinder pressure 3; 4: cooler 4; 5: chamber; 6: turn quiet dish chamber; 7: turbine rotor blade; 8: outer shell; 9: inner casing; 10: bearing; 11: bleed hole; 12: breathing pipe; 13: rotor; 14: heat insulating tube; 14a: flange; 14b: annular boss; 14c: heat insulating tube pipe shaft.
Embodiment
Below in conjunction with drawings and Examples, embodiment of the present utility model is described in further detail.Following instance for illustration of the utility model, but is not used for limiting scope of the present utility model.
In description of the present utility model, it should be noted that, term " " center ", " longitudinal direction ", " transverse direction ", " on ", D score, " front ", " afterwards ", " left side ", " right side ", " vertically ", " level ", " top ", " end " " interior ", orientation or the position relationship of the instruction such as " outward " are based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as restriction of the present utility model.
In description of the present utility model, it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals.For the ordinary skill in the art, concrete condition the concrete meaning of above-mentioned term in the utility model can be understood.
In addition, in description of the present utility model, except as otherwise noted, the implication of " multiple ", " many ", " many groups " is two or more.
Embodiment one
As shown in Figure 2, for a kind of gas turbine combustion cylinder pressure 3 heat-insulating structure that the utility model provides, described combustion cylinder pressure 3 comprises outer shell 8 and inner casing 9, described inner casing 9 and outer shell 8 form the chamber 5 of combustion cylinder pressure 3 jointly, the multiple bearings 10 connecting outer shell 8 and inner casing 9 are provided with in described chamber 5, be connected as a whole by described inner casing 9 with outer shell 8 by described bearing 10, be also provided with firing chamber 2 in described chamber 5, multiple described bearings 10 are distributed on the circumference of described firing chamber 2; Be provided with the bleed hole 11 being communicated with described outer shell 8 and inner casing 9 in bearing 10 described at least one, in described bleed hole 11, be provided with heat insulating tube 14, the heat exchange effectively can isolated the cold air in bleed hole 11 and fire between cylinder pressure 3 chamber, thus avoid the generation of thermal stress; The inlet end of described heat insulating tube 14 and the suction port in described bleed hole 11 are connected, and leave gap between the pipe shaft of described heat insulating tube 14 and described bleed hole 11; Therefore at expanded by heating or can free deformation by described heat insulating tube 14 during cold events, and then avoid between described heat insulating tube 14 and bearing 10 and produce excessive thermal stress.
Conveniently heat insulating tube 14 is reliably connected with bleed hole 11, as shown in Figure 3, the inlet end of described heat insulating tube 14 is provided with annular boss 14b, and the inlet end of described heat insulating tube 14 is connected by the suction port in described annular boss 14b and described bleed hole 11, is convenient to location; Gas compressor 1 exit gas enters cooler 4, through entering heat insulating tube 14 by breathing pipe 12 after cooling, importing and turning quiet dish chamber 6, entering turbine and cool.
Conveniently install, the top of the inlet end of described heat insulating tube 14 is provided with flange 14a; Described combustion cylinder pressure 3 is provided with breathing pipe 12 and cooler 4, and the two ends of described cooler 4 are communicated with described outer shell by described breathing pipe 12, and the outlet side of described breathing pipe 12 is connected by flange 14a with the inlet end of described heat insulating tube 14.
Preferably, described heat insulating tube 14 is made as Cr18Ni9 for stainless steel, and the outer surface of described heat insulating tube 14 is enclosed with thermal-protective material, to reduce heat conduction further.
Embodiment two
Embodiment two is only with the difference of embodiment one, and as shown in Figure 4, described heat insulating tube pipe shaft 14c is also interval with one or more described annular boss 14b along its length, prevents longer heat insulating tube 14 from producing vibration and fatigue fracture.
Embodiment three
Embodiment three is only with the difference of embodiment one, and as shown in Figure 5, the outer surface being positioned at the one or more described annular boss 14b on described heat insulating tube pipe shaft 14c is circular arc, to reduce heat transfer further.
As can be seen from the above embodiments, the utility model can effectively isolate bleed hole
Cold air in 11 and the heat exchange between combustion cylinder pressure 3, avoid the generation of thermal stress; Meanwhile,
Heat insulating tube 14 also possesses the ability of free deformation, to avoid heat insulating tube 14 and bearing 10
Between produce excessive thermal stress.
The foregoing is only preferred embodiment of the present utility model; not in order to limit the utility model; all within spirit of the present utility model and principle, any amendment done, equivalent replacement, improvement etc., all should be included within protection domain of the present utility model.
Claims (8)
1. a gas turbine combustion cylinder pressure heat-insulating structure, described combustion cylinder pressure comprises outer shell and inner casing, described inner casing and outer shell form the chamber of combustion cylinder pressure jointly, the multiple bearings connecting outer shell and inner casing are provided with in described chamber, the bleed hole being communicated with described outer shell and inner casing is provided with in bearing described at least one, it is characterized in that, heat insulating tube is provided with in described bleed hole, the inlet end of described heat insulating tube and the suction port in described bleed hole are connected, and leave gap between the pipe shaft of described heat insulating tube and described bleed hole.
2. gas turbine combustion cylinder pressure heat-insulating structure as claimed in claim 1, it is characterized in that, the inlet end of described heat insulating tube is provided with annular boss, and the inlet end of described heat insulating tube is connected by the suction port in described annular boss and described bleed hole.
3. gas turbine combustion cylinder pressure heat-insulating structure as claimed in claim 1, it is characterized in that, the top of the inlet end of described heat insulating tube is provided with flange.
4. gas turbine combustion cylinder pressure heat-insulating structure as claimed in claim 3, it is characterized in that, described combustion cylinder pressure is provided with breathing pipe and cooler, the two ends of described cooler are communicated with described outer shell by described breathing pipe, and the outlet side of described breathing pipe and the inlet end of described heat insulating tube pass through Flange joint.
5. gas turbine combustion cylinder pressure heat-insulating structure as claimed in claim 2, it is characterized in that, the pipe shaft of described heat insulating tube is interval with one or more described annular boss along its length.
6. gas turbine combustion cylinder pressure heat-insulating structure as claimed in claim 5, it is characterized in that, the outer surface being positioned at the one or more described annular boss on described heat insulating tube pipe shaft is circular arc.
7. the gas turbine combustion cylinder pressure heat-insulating structure as described in any one of claim 1-6, it is characterized in that, the outer surface of described heat insulating tube is enclosed with thermal-protective material.
8. gas turbine combustion cylinder pressure heat-insulating structure as claimed in claim 1, it is characterized in that, described heat insulating tube is that stainless steel is made.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520069507.2U CN204591376U (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine combustion cylinder pressure heat-insulating structure |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201520069507.2U CN204591376U (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine combustion cylinder pressure heat-insulating structure |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN204591376U true CN204591376U (en) | 2015-08-26 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201520069507.2U Withdrawn - After Issue CN204591376U (en) | 2015-01-30 | 2015-01-30 | A kind of gas turbine combustion cylinder pressure heat-insulating structure |
Country Status (1)
| Country | Link |
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| CN (1) | CN204591376U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104675454A (en) * | 2015-01-30 | 2015-06-03 | 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 combustion pressure cylinder thermal insulation structure |
-
2015
- 2015-01-30 CN CN201520069507.2U patent/CN204591376U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104675454A (en) * | 2015-01-30 | 2015-06-03 | 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 combustion pressure cylinder thermal insulation structure |
| CN104675454B (en) * | 2015-01-30 | 2019-10-01 | 北京华清燃气轮机与煤气化联合循环工程技术有限公司 | A kind of gas turbine combustion cylinder pressure heat insulation structural |
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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 combustion pressure cylinder thermal insulation structure Effective date of registration: 20161104 Granted publication date: 20150826 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 | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20150826 Effective date of abandoning: 20191001 |
|
| AV01 | Patent right actively abandoned |
Granted publication date: 20150826 Effective date of abandoning: 20191001 |
|
| 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: 20150826 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |