CN204313312U - A kind of term durability gas turbine flame barrel - Google Patents
A kind of term durability gas turbine flame barrel Download PDFInfo
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- CN204313312U CN204313312U CN201420681422.5U CN201420681422U CN204313312U CN 204313312 U CN204313312 U CN 204313312U CN 201420681422 U CN201420681422 U CN 201420681422U CN 204313312 U CN204313312 U CN 204313312U
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- gas turbine
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- term durability
- deflector
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Abstract
The utility model relates to gas turbine field, is specifically related to a kind of term durability gas turbine flame barrel.This term durability gas turbine flame barrel comprises cylindrical shell and cover cap, and described cover cap is arranged on one end of cylindrical shell, described cylindrical shell be provided with make mixed gas flow to into the first blending hole; This term durability gas turbine flame barrel also comprises viscous flow plate and deflector, and described viscous flow plate and deflector surround guiding region in cylindrical shell, and described guiding region flows to predeterminated position for guiding described mixed gas.Blending air-flow can be guided to the position needing blending by this term durability gas turbine flame barrel, can keep or promote the regulating effect to burner inner liner combustor exit temperature field when blending tolerance reduces; And, also can strengthen the mixability of main flow combustion gas and blending air-flow in burner inner liner, reduce the phenomenon that burner inner liner combustor exit temperature is uneven.
Description
Technical field
The utility model relates to gas turbine field, particularly relates to a kind of term durability gas turbine flame barrel.
Background technology
At present, combustion chamber flame drum is one of parts that in gas turbine, price is the most expensive, working environment is the most severe, the life-span is the shortest, and the demand of the fuel gas temperature demand fulfillment turbine inlet temperature of gas-turbine combustion chamber outlet.To the important regulating measure of this Temperature Distribution be by participating in burning in combustion chamber, air beyond cooling procedure noted into burner inner liner by several blending hole of flame drum tail, and then regulates the radial distribution of temperature.But under specific operation, because the flow of inlet air and fuel, temperature are determined value, so outlet mean temperature is also determined value, and the ratio of dilution air is larger, means that Exit temperature distribution is more unequal.And gas turbine is pursue higher overall efficiency, most effective method improves combustor exit temperature, i.e. combustion gas initial temperature exactly.This means to need under same power, have air more at high proportion to need to participate in burning, simultaneously because temperature raises, also needing air more at high proportion needs to cool.This kind of trend result in air less and less can be used for blending, and visible original blending hole structure can not adjust combustor exit fuel gas temperature effectively.
Therefore, for above deficiency, need a kind ofly under the condition reducing blending tolerance, effectively dilution air to be dispensed to target location, thus the term durability gas turbine flame barrel that Exit temperature distribution can be avoided uneven.
Utility model content
(1) technical problem that will solve
The technical problems to be solved in the utility model there is provided a kind of term durability gas turbine flame barrel, makes it possible to, under the condition reducing blending tolerance, effectively dilution air is dispensed to target location, thus the situation that Exit temperature distribution can be avoided uneven.
(2) technical scheme
In order to solve the problems of the technologies described above, the term durability gas turbine flame barrel that the utility model provides comprises cylindrical shell and cover cap, and described cover cap is arranged on one end of cylindrical shell, described cylindrical shell be provided with make mixed gas flow to into the first blending hole; This term durability gas turbine flame barrel also comprises viscous flow plate and deflector, and described viscous flow plate and deflector surround guiding region in cylindrical shell, and described guiding region flows to predeterminated position for guiding described mixed gas.
Wherein, described viscous flow plate be fixed on cylindrical shell inwall on and between the first blending hole and cover cap; One end of described deflector is connected on viscous flow plate, and the other end is along extending near the direction of the first blending hole.
Wherein, described deflector is provided with multiple second blending hole.
Wherein, the angle between described deflector and tubular axis is 3 °-10 °.
Wherein, described viscous flow plate is connected with vertical between cylinder inboard wall.
Wherein, described viscous flow plate along the length of cylindrical shell radial direction between 1/10 radius and 1/2 radius of cylindrical shell.
Wherein, the distance of described viscous flow plate distance the first blending hole center line is 0.1 ~ 1 times of the first blending hole radius; The distance of the spread ends distance first blending hole center line of described deflector is 1 ~ 5 times of the first blending hole radius.
Wherein, described viscous flow plate and deflector are respectively equipped with multiple diffusion cooling hole.
Wherein, the aperture of described diffusion cooling hole is 1mm-1.5mm.
Wherein, the wall of described cylindrical shell is also provided with primary holes and cooling through hole.
(3) beneficial effect
Technique scheme of the present utility model has following beneficial effect: the gas-turbine combustion chamber burner inner liner that the utility model relates to, surrounds guiding region by viscous flow plate and deflector in cylindrical shell, thus blending air-flow can be guided to the position needing blending.Even if under the condition that blending tolerance reduces, adopt the burner inner liner of this structure still can keep even promoting the regulating effect to burner inner liner combustor exit temperature field; Meanwhile, this burner inner liner can strengthen the mixability of main flow combustion gas and blending air-flow in burner inner liner greatly, and then reduces the uneven phenomenon of combustor exit temperature that blending hole structure in the past brings.
Accompanying drawing explanation
Fig. 1 is the structural representation of the utility model embodiment term durability gas turbine flame barrel;
Fig. 2 is the connection diagram of the utility model embodiment viscous flow plate and deflector;
Fig. 3 is the stereogram of the utility model embodiment term durability gas turbine flame barrel.
Wherein, 2: cover cap; 3: cylindrical shell; 4: primary holes; 5: cooling through hole; 6: the first blending hole; 61: viscous flow plate; 62: deflector; 63: the second blending hole; 64: diffusion cooling hole.
Detailed description of the invention
Below in conjunction with drawings and Examples, embodiment of the present utility model is described in further detail.Following examples for illustration of the utility model, but can not be used for limiting scope of the present utility model.
In description of the present utility model, except as otherwise noted, the implication of " multiple " is two or more; Term " on ", D score, "left", "right", " interior ", " outward ", " front end ", " rear end ", " head ", the orientation of the instruction such as " afterbody " or position relationship be based on orientation shown in the drawings or position relationship, only the utility model and simplified characterization for convenience of description, instead of the device of instruction or hint 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 addition, term " first ", " second ", " the 3rd " etc. only for describing object, and can not be interpreted as instruction or hint relative importance.
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.For the ordinary skill in the art, concrete condition the concrete meaning of above-mentioned term in the utility model can be understood.
As Figure 1-3, the term durability gas turbine flame barrel that the present embodiment provides, comprise cylindrical shell 3 and cover cap 2, cover cap 2 is arranged on one end of cylindrical shell 3, and main flow combustion gas can enter in cylindrical shell 3 from the side of cover cap 2.Cylindrical shell 3 is provided with for make mixed gas flow to into the first blending hole 6, certainly, the wall of cylindrical shell 3 is also provided with multiple primary holes 4 and cooling through hole 5.And the quantity of the first blending hole 6, primary holes 4 and cooling through hole 5 is not limited to specific quantity, and visual actual conditions adjust flexibly; And, this burner inner liner also comprises viscous flow plate 61 and deflector 62, viscous flow plate 61 and deflector 62 are all arranged in cylindrical shell 3, and guiding region is surrounded in cylindrical shell 3, guiding region flow to predeterminated position for guiding mixed gas, such as: bootable mixed gas flows on the right side of viscous flow plate 61 and flows into, namely, the position of combustor exit, and with the main flow gas mixing in burner inner liner; Certainly, blending air-flow also can flow out this region by the second blending hole 63 on deflector 62, and with the main flow gas mixing in burner inner liner.
As can be seen here, acting as of the guiding region in the present embodiment: on the one hand, can guide to the position needing blending by blending air-flow, keeps or promote the regulating effect to burner inner liner combustor exit temperature field when blending tolerance reduces; On the other hand, strengthen the immixture of main flow combustion gas and blending air-flow in burner inner liner, reduce the phenomenon that burner inner liner combustor exit temperature is uneven.
Be worth illustrating, viscous flow plate 61, the guiding region surrounded between deflector 62 and cylindrical shell 3 inwall can be various shape, as long as blending air-flow can be guided to predeterminated position.Be described with wherein a kind of preferred embodiment: viscous flow plate 61 is connected on the inwall of cylindrical shell 3, and viscous flow plate 61 is between the first blending hole 6 and cover cap 2; And one end of deflector 62 is connected on viscous flow plate 61, the other end, along extending near the direction of the first blending hole 6, is tilt distribution for cylindrical shell 3 is axial.Wherein, viscous flow plate 61 for be welded to connect or metal plate punching is connected, and can be welded on cylindrical shell 3 inwall by viscous flow plate 61 and deflector 62.
And, deflector 62 is also provided with multiple second blending hole 63, jet can be penetrated process and separate with blending procedure, thus realize the controllability to blending procedure, reach more stable mixing effect.Wherein, the second blending hole 63 is the uniform or non-uniform hole of several axis, and pass can be slotted eye or the circular port of long axis circumference, thus can regulate blending according to Actual combustion room burner inner liner combustion situation.Such as: if need larger blending area, then long axis circumference slotted eye is adopted; If need dilution air more concentrated, then adopt circular air admission hole.
Further, the angle between deflector 62 and cylindrical shell 3 axis is 3 °-10 °, and this deflector 62 be obliquely installed can be expanded the main flow combustion gas in cylindrical shell 3, accelerates the blending of blending gas and main flow combustion gas.
Correspondingly, can be connected for vertical between viscous flow plate 61 with cylindrical shell 3 inwall, can ensure that blending air-flow has certain depth of penetration.
Be specially: viscous flow plate 61 along the length of cylindrical shell 3 radial direction between 1/10 radius and 1/2 radius of cylindrical shell 3, namely, the distance be embedded in cylindrical shell 3 of viscous flow plate 61 is more than or equal to 1/10 radius, and be less than or equal to 1/2 radius, thus the depth of penetration of blending air-flow can be ensured, reach good mixing effect.
Wherein, in implementation process, stream plate 61 can adjust flexibly with the concrete proportional sizes of deflector 62, such as: viscous flow plate 61 is 0.1 ~ 1 times of the first blending hole 6 radius apart from the distance of the first blending hole 6 center line; The distance of spread ends distance first blending hole 6 center line of deflector 62 is 1 ~ 5 times of the first blending hole 6 radius, can ensure more effective guiding distance, conveniently blending air-flow is transported to target location.
Viscous flow plate 61 with deflector 62 are also respectively equipped with multiple diffusion cooling hole 64, can cool the wall of viscous flow plate 61 and deflector 62 itself, the aperture of diffusion cooling hole 64 is 1mm-1.5mm, and the shape of diffusion cooling hole 64, angle can be various ways.In addition, for viscous flow plate 61 and deflector 62, material behavior under the material at high temperature environment adopted should reach or be better than GH536 or GH163 respective level, guarantees in high-temperature fuel gas, and this structure is unlikely to be burned and ensures the service life identical with burner inner liner.
This term durability gas turbine flame barrel course of work is as follows: first, the guiding region that blending air-flow (air) enters viscous flow plate 61 through the first blending hole 6, deflector 62 is formed with burner inner liner wall; Then, a part of blending air-flow flows out this region backward along deflector 62, and with the main flow gas mixing in burner inner liner; The second blending hole 63 that another part mixed gas flows through on deflector 62 flows out this region, and with the main flow gas mixing in burner inner liner; Finally, all the other mixed gases diffusion cooling hole 64 flowed through on viscous flow plate 61, deflector 62 flows out to cool its wall.
In sum, the gas-turbine combustion chamber burner inner liner that the utility model relates to, surrounds guiding region by viscous flow plate and deflector in cylindrical shell, thus blending air-flow can be guided to the position needing blending.Even if under the condition that blending tolerance reduces, adopt the burner inner liner of this structure still can keep even promoting the regulating effect to burner inner liner combustor exit temperature field; Meanwhile, this burner inner liner can strengthen the mixability of main flow combustion gas and blending air-flow in burner inner liner greatly, and then reduces the uneven phenomenon of combustor exit temperature that blending hole structure in the past brings.
Embodiment of the present utility model provides for the purpose of example and description, and is not exhaustively or by the utility model be limited to disclosed form.Many modifications and variations are apparent for the ordinary skill in the art.Selecting and describing embodiment is in order to principle of the present utility model and practical application are better described, and enables those of ordinary skill in the art understand the utility model thus design the various embodiments with various amendment being suitable for special-purpose.
Claims (10)
1. a term durability gas turbine flame barrel, comprise cylindrical shell (3) and cover cap (2), described cover cap (2) is arranged on one end of cylindrical shell (3), described cylindrical shell (3) be provided with make mixed gas flow to into the first blending hole (6); It is characterized in that, also comprise viscous flow plate (61) and deflector (62), described viscous flow plate (61) and deflector (62) surround guiding region in cylindrical shell (3), and described guiding region flows to predeterminated position for guiding described mixed gas.
2. term durability gas turbine flame barrel according to claim 1, is characterized in that, the inwall that described viscous flow plate (61) is fixed on cylindrical shell (3) is positioned between the first blending hole (6) and cover cap (2); One end of described deflector (62) is connected on viscous flow plate (61), and the other end is along extending near the direction of the first blending hole (6).
3. term durability gas turbine flame barrel according to claim 2, is characterized in that, described deflector (62) is provided with multiple second blending hole (63).
4. term durability gas turbine flame barrel according to claim 2, is characterized in that, the angle between described deflector (62) and cylindrical shell (3) axis is 3 °-10 °.
5. term durability gas turbine flame barrel according to claim 2, is characterized in that, described viscous flow plate (61) is connected with vertical between cylindrical shell (3) inwall.
6. term durability gas turbine flame barrel according to claim 5, is characterized in that, described viscous flow plate (61) along the radial length of cylindrical shell (3) between 1/10 radius and 1/2 radius of cylindrical shell (3).
7. term durability gas turbine flame barrel according to claim 2, is characterized in that, the distance of described viscous flow plate (61) distance the first blending hole (6) center line is 0.1 ~ 1 times of the first blending hole (6) radius; The distance of spread ends distance the first blending hole (6) center line of described deflector (62) is 1 ~ 5 times of the first blending hole (6) radius.
8. term durability gas turbine flame barrel according to claim 1, is characterized in that, described viscous flow plate (61) and deflector (62) are respectively equipped with multiple diffusion cooling hole (64).
9. term durability gas turbine flame barrel according to claim 8, is characterized in that, the aperture of described diffusion cooling hole (64) is 1mm-1.5mm.
10. term durability gas turbine flame barrel according to claim 1, is characterized in that, the wall of described cylindrical shell (3) is also provided with primary holes (4) and cooling through hole (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420681422.5U CN204313312U (en) | 2014-11-11 | 2014-11-11 | A kind of term durability gas turbine flame barrel |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420681422.5U CN204313312U (en) | 2014-11-11 | 2014-11-11 | A kind of term durability gas turbine flame barrel |
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| CN204313312U true CN204313312U (en) | 2015-05-06 |
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| CN201420681422.5U Active CN204313312U (en) | 2014-11-11 | 2014-11-11 | A kind of term durability gas turbine flame barrel |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107062306A (en) * | 2017-05-09 | 2017-08-18 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
| CN110736109A (en) * | 2019-09-29 | 2020-01-31 | 中国航发沈阳发动机研究所 | flame tube beneficial to adjusting temperature field of outlet of combustion chamber |
| CN113091093A (en) * | 2021-05-13 | 2021-07-09 | 中国联合重型燃气轮机技术有限公司 | Air dome and nozzle for gas turbine |
| CN114688560A (en) * | 2022-03-09 | 2022-07-01 | 中国联合重型燃气轮机技术有限公司 | Mixer for staged combustion chamber |
-
2014
- 2014-11-11 CN CN201420681422.5U patent/CN204313312U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107062306A (en) * | 2017-05-09 | 2017-08-18 | 上海泛智能源装备有限公司 | A kind of combustion chamber and gas turbine |
| CN110736109A (en) * | 2019-09-29 | 2020-01-31 | 中国航发沈阳发动机研究所 | flame tube beneficial to adjusting temperature field of outlet of combustion chamber |
| CN113091093A (en) * | 2021-05-13 | 2021-07-09 | 中国联合重型燃气轮机技术有限公司 | Air dome and nozzle for gas turbine |
| CN114688560A (en) * | 2022-03-09 | 2022-07-01 | 中国联合重型燃气轮机技术有限公司 | Mixer for staged combustion chamber |
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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: Combustion gas turbine flame tube mixer high temperature alloy vacuum argon filling protecting welding method Effective date of registration: 20161104 Granted publication date: 20150506 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 |
Date of cancellation: 20191211 Granted publication date: 20150506 Pledgee: Tsinghua Holdings Co., Ltd. Pledgor: Beijing Huatsing Gas Turbine & IGCC Technology Co., Ltd. Registration number: 2016990000853 |
|
| PC01 | Cancellation of the registration of the contract for pledge of patent right |