CN212157263U - Supporting device for gas turbine combustion chamber transition section impact sleeve - Google Patents
Supporting device for gas turbine combustion chamber transition section impact sleeve Download PDFInfo
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- CN212157263U CN212157263U CN202020393827.4U CN202020393827U CN212157263U CN 212157263 U CN212157263 U CN 212157263U CN 202020393827 U CN202020393827 U CN 202020393827U CN 212157263 U CN212157263 U CN 212157263U
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Abstract
The utility model discloses a strutting arrangement for be used for gas turbine combustion chamber changeover portion to strike cover, belong to gas turbine technical field, this strutting arrangement makes changeover portion inlayer and impact cover form the support that can slide in the entrance, including supporting a section of thick bamboo, the hood, be equipped with the spring in the support section of thick bamboo, the upper and lower end of spring has set up gasket and lower gasket respectively, go up a gasket jack-up and support the head, support the head and stretch out from the through-hole of hood under the effect of spring prestressing force, it has the cambered surface to support the head top, it closely laminates and can slide to overlap the inboard with the changeover portion impact, can keep supporting the column cap and the changeover portion impact the cover inboard closely laminate and unlikely contact pressure too big and block, can avoid producing stress concentration and fracture, dismantle the convenience during this strutting arrangement maintenance simultaneously, the convenience of use is strong.
Description
Technical Field
The utility model belongs to the technical field of gas turbine, concretely relates to a strutting arrangement that is used for gas turbine combustion chamber changeover portion to strike cover.
Background
The gas turbine is divided from the whole structure and mainly comprises a compressor, a combustion chamber and a turbine section, wherein the combustion chamber is an area for burning fuel and realizing energy conversion, and therefore the combustion chamber needs to be made of high-temperature-resistant materials; hot gas generated after combustion of the combustion gas enters the transition section from the combustion chamber and then enters the turbine section, so that the turbine is driven to generate power.
In chinese patent application CN102620294A (transition piece impingement sleeve for gas turbine), a typical impingement sleeve structure is disclosed, which comprises a first casing surrounding a portion of an inner duct of the transition section and a second casing configured to surround a portion of the inner duct, wherein the first casing and the second casing are connected by a fastener, and the impingement sleeve can be detachably mounted by locking or unlocking the fastener, which is convenient for use. The main function of the impingement sleeve at the transition section is to provide impingement cooling for the inner duct, and therefore the impingement sleeve is typically provided with a plurality of cooling holes, but the impingement sleeve is highly susceptible to damage from shock and thermal expansion from fuel combustion, and therefore a support means is required for the transition section impingement sleeve to protect the impingement sleeve.
The transition section of the gas turbine combustion chamber designed at home at present generally adopts a structure with a double-layer impact sleeve, and a circle of support is arranged at an inlet between the transition section impact sleeve and an inner layer. Conventional designs may include a support ring and inelastic spacers between the impingement sleeve and the transition piece, but the spacers are very limited in their effectiveness because they are inelastic and cannot withstand structural shock and thermal expansion.
Chinese patent application CN102620313A (support between a transition piece and an impingement sleeve in a combustor), in which a support is provided between the transition piece and the impingement sleeve of the combustor, wherein the support includes an elastic portion for providing damping between the transition piece and the impingement sleeve, a mounting portion for mounting the support to one of the transition piece or the impingement sleeve, and a contact portion for contacting the other of the transition piece or the impingement sleeve, the support of this structure is capable of resisting structural vibration and thermal expansion between the support ring and the transition piece, thereby avoiding cracking of the support ring, the impingement sleeve and the transition piece, and further enabling the structure of the gas turbine to be more stable. However, in the present invention, the structure of the supporting member is easily cracked by stress concentration at the fillet, thereby shortening the service life.
Therefore, in order to improve the service performance of the gas turbine, a supporting device of the gas turbine combustor transition section impact sleeve, which has a simple structure and a long service life, needs to be designed to meet industrial requirements.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the technical problem that the gas turbine combustion chamber changeover portion among the prior art strikes strutting arrangement of cover has technical problem such as life weak point, structure complicacy, manufacturing cost height.
In order to solve the technical problem, the utility model discloses a supporting device of a gas turbine combustor transition section impact sleeve, which can enable the transition section inner layer and the impact sleeve to form a slidable support at an inlet and is positioned between the gas turbine combustor transition section inner layer and the gas turbine combustor transition section impact sleeve, wherein the supporting device of the gas turbine combustor transition section impact sleeve is provided with a plurality of supporting devices which are circumferentially and symmetrically arranged on an outer ring of the inlet section of the inner layer of the gas turbine combustor transition section;
the supporting device of the impact sleeve of the transition section of the combustion chamber of the gas turbine comprises a supporting cylinder and a hood;
the support cylinder is positioned on an outer ring of an inner inlet section of a transition section of the combustion chamber of the gas turbine; the hood is positioned at one end of the support cylinder, which is far away from the inner layer of the transition section of the combustion chamber of the gas turbine, and is connected with the support cylinder; the inner diameter of the hood is equal to the outer diameter of the support cylinder;
a lower gasket is arranged at one end of the inner layer of the transition section of the combustion chamber of the gas turbine in the supporting cylinder, a spring is arranged on the lower gasket, and an upper gasket is arranged at one end, far away from the lower gasket, of the spring;
a supporting head is arranged on one side of the upper gasket, which is far away from the spring;
one side of the hood, which is far away from the support cylinder, is provided with a through hole; one part of the supporting head is positioned in a space formed between the supporting head and the supporting barrel, and the other part of the supporting head penetrates through the through hole, is positioned outside the hood and is contacted with the impact sleeve of the transition section of the combustion chamber of the gas turbine.
Furthermore, the supporting head is a supporting column head, and the supporting column head is in an inverted T shape. Furthermore, one end of the support head, facing the gas turbine combustion chamber transition section impact sleeve, is designed to be an arc surface, and the curvature of the arc surface is smaller than that of the gas turbine combustion chamber transition section impact sleeve.
Further, the support head is spherical; the curvature of the sphere is smaller than that of the impact sleeve of the transition section of the combustion chamber of the gas turbine. Furthermore, the upper gasket is a curved gasket, and the curvature of the curved gasket is smaller than that of the support head.
Further, the supporting cylinder is welded on an outer ring of an inner layer inlet section of a transition section of the gas turbine combustor.
Furthermore, the hood is sleeved at the upper end of the support barrel in a threaded connection mode. Furthermore, the part of the support cylinder connected with the hood is provided with an external thread; the part of the hood, which is connected with the support cylinder, is provided with internal threads; the external thread on the supporting cylinder is matched with the internal thread on the hood,
further, the outer diameter of the lower gasket is equal to the inner diameter of the support cylinder. Further, the outer diameter of the upper gasket is smaller than that of the lower gasket.
The supporting column head of the supporting device extends out of the through hole of the hood under the action of the prestress of the spring, and the top of the supporting column head is provided with a cambered surface which is tightly attached to the inner side of the transition section impact sleeve and can slide. At the moment, the inner layer of the transition section keeps a stable floating state under the resultant force of a plurality of supporting devices in a whole circle.
When the transition section is in a working state, the outlet of the transition section is connected to a first-stage turbine stator blade ring and is regarded as a dead point, the inner layer of the transition section and the impact sleeve are expanded forwards, and the working temperature of the inner layer is higher than that of the impact sleeve, so that the axial expansion amount and the radial expansion amount of the inner layer of the transition section relative to the impact sleeve are large. At the moment, relative displacement is generated between the inner layer of the transition section and the impact sleeve in the axial direction and the radial direction. When axial displacement exists, the inner layer of the transition section is connected with the supporting device and slides forwards along the axis to compensate; when radial displacement occurs, the distance between the annular seam between the inner layer of the transition section and the impact sleeve is reduced, at the moment, the supporting column head retracts into the supporting cylinder and compresses the spring, and the supporting column head is still kept to be tightly attached to the inner side of the impact sleeve of the transition section and cannot be jammed due to overlarge contact pressure.
The supporting device is welded on the outer side of the inner layer of the transition section through the bottom of the supporting cylinder, a whole circle of welding seam is adopted for welding, and the size of the supporting cylinder is relatively small, so that the stress generated by the whole welding seam due to temperature change is much smaller than that generated by welding at two ends of a 'n' -shaped support in the prior art, and the problem of cracking caused by stress concentration is avoided.
Compared with the prior art, the utility model discloses a strutting arrangement of cover is strikeed to combustion chamber changeover portion has following advantage:
(1) the utility model discloses a gas turbine combustion chamber changeover portion strikes strutting arrangement of cover can provide bigger displacement compensation ability for "nearly" font support commonly used, has avoided the changeover portion inlayer to take the support because radial expansion is too big and take place the jam with strikeing the cover, is also difficult for appearing stress concentration and leads to the condition of fracture in support leg department simultaneously, can prolong the life-span of supporting.
(2) The utility model discloses a gas turbine combustion chamber changeover portion strikes strutting arrangement of cover simple structure, low in manufacturing cost, and it is convenient to overhaul, consequently also has comparable economic benefits.
(3) The utility model discloses a supporting arrangement of gas turbine combustion chamber changeover portion impact cover only needs to twist off the hood of taking internal screw thread from supporting a section of thick bamboo when maintaining, takes out the spring, goes up the gasket, supports the head, if have damage directly change new part install can, the operation is more convenient relatively.
Drawings
FIG. 1: the gas turbine combustor transition section is arranged in a schematic view.
FIG. 2: the B direction structure in figure 1 is schematically shown.
FIG. 3: the prior art is a structural schematic diagram of a support device shaped like a Chinese character 'ji'.
FIG. 4: the supporting device of the combustor transition section impact sleeve in the embodiment 1 is schematically shown.
FIG. 5: an enlarged view of the support head in fig. 4.
FIG. 6: the supporting device of the combustor transition section impact sleeve in the embodiment 2 is schematically shown.
Description of reference numerals: 1-transition section impact sleeve, 2-transition section inner layer, 3-inverted V-shaped support, 6-hood, 7-spring, 8-support cylinder, 9-support column head, 10-upper gasket, 11-lower gasket, 12-support ball head, 13-curved gasket, 16-compressor cylinder, 17-turbine cylinder, 18-combustion chamber casing, 19-flame cylinder, 20-turbine first-stage stationary blade ring and 21-transition section support frame.
Detailed Description
The following detailed description of the embodiments of the present invention will be made with reference to the accompanying drawings.
The terms of orientation such as "upper", "lower", "left", "right", "front" and "back" mentioned in this section are only used to describe the relative position of the components of the product in this specific embodiment, and should not be interpreted as limiting the terms of the present invention.
As shown in fig. 1, a schematic diagram of an arrangement structure of a transition section of a gas turbine combustor, and fig. 2-3 are schematic diagrams of a support device of an impact sleeve of a transition section of a gas turbine combustor in the prior art, an outlet of the transition section is fixed on a first-stage turbine stationary blade ring 20 through bolts, a transition section support frame 21 is arranged on an impact sleeve at an inlet of the transition section to fix the transition section on a compressor cylinder 16, the impact sleeve surrounds an inner layer 2 of the transition section through a plurality of n-shaped supports 3 welded on the inner layer, because a temperature difference between the inner layer 2 and the impact sleeve 1 is large during working, the thermal expansion amounts of the two are different and generate large radial and axial displacement, the inner layer 2 and the n-shaped supports 3 move forward along the axis of a flame tube 19 together, and expand outward in the radial direction. The inner layer 2 has larger radial expansion deformation than the impact sleeve 1, and can cause the jamming of the top surface of the inverted V-shaped support 3 and the inner layer of the impact sleeve. The support in the shape of the Chinese character 'ji' is easy to crack due to stress concentration when welded at the welding feet at two sides, and the service life is influenced.
Example 1
Fig. 4 is a schematic structural view of a support device of the gas turbine combustor transition section impingement sleeve of embodiment 1, and fig. 5 is an enlarged view of a support head. The support section of thick bamboo 8 welded fastening that the changeover portion strikes the cover and supports is in the outer lane of changeover portion inlayer entry, has set up lower gasket 11 in the support section of thick bamboo 8, is equipped with spring 7 on the lower gasket, and there is last gasket 10 spring 7 upper end, and last gasket is pushing up support column cap 9, and support column cap 9 is injectd inside support section of thick bamboo 8 by a hood 6, and hood 9 and support section of thick bamboo 8 adopt threaded connection. Support column cap 9 and changeover portion impact cover 1 inboard closely laminate, when changeover portion inlayer 2 is being heated the expansion and is moving forward along the axial, and the company takes strutting arrangement outwards to slide together, when radially taking place the inflation, the changeover portion strikes the interval of cover 1 and changeover portion inlayer 2 and can diminish, supports the column cap 9 this moment and contracts and compression spring 7 to 8 in the support cylinder. Therefore, the supporting column head 9 and the transition section impact sleeve 1 can still be kept in a close fit state, and the phenomenon that the supporting column head 9 and the impact sleeve 1 generate excessive extrusion stress to cause jamming due to excessive radial expansion can also be prevented. The spring 7 is designed according to the required prestress, and the length of the support column head 9 extending out of the hood 6 ensures that the hood 6 does not interfere with the transition section impact sleeve 1 during cold and hot state calculation.
Example 2
Fig. 6 is a schematic structural diagram of a supporting device of the gas turbine combustor transition section impingement sleeve of embodiment 2, specifically, the supporting column head 9 in embodiment 1 is replaced by a supporting bulb 12, and the upper gasket 10 is replaced by a curved gasket 13. The supporting ball head is limited in the supporting barrel by the hood 6, the supporting ball head can rotate in a space limited by the curved gasket 13 and the hood 6, and the supporting ball head can retract into the supporting barrel 8 under the extrusion of the inner side of the transition section impact sleeve 1.
The above-mentioned series of detailed descriptions are only specific descriptions of feasible embodiments of the present invention, and they are not intended to limit the scope of the present invention, and all the changes made without departing from the spirit of the present invention within the knowledge range of the ordinary skilled person in the art are within the scope of the present invention.
Claims (10)
1. The utility model provides a strutting arrangement for be used for gas turbine combustor changeover portion to strike cover, is located between gas turbine combustor changeover portion inlayer and the gas turbine combustor changeover portion impact cover, its characterized in that:
the supporting devices of the impact sleeves of the transition section of the gas turbine combustion chamber are multiple and are circumferentially and symmetrically arranged on the outer ring of the inlet section of the inner layer of the transition section of the gas turbine combustion chamber;
the supporting device of the impact sleeve of the transition section of the combustion chamber of the gas turbine comprises a supporting cylinder and a hood;
the support cylinder is positioned on an outer ring of an inner inlet section of a transition section of the combustion chamber of the gas turbine; the hood is positioned at one end of the support cylinder, which is far away from the inner layer of the transition section of the combustion chamber of the gas turbine, and is connected with the support cylinder; the inner diameter of the hood is equal to the outer diameter of the support cylinder;
a lower gasket is arranged at one end of the inner layer of the transition section of the combustion chamber of the gas turbine in the supporting cylinder, a spring is arranged on the lower gasket, and an upper gasket is arranged at one end, far away from the lower gasket, of the spring;
a supporting head is arranged on one side of the upper gasket, which is far away from the spring; one end of the supporting head, which faces the transition section impact sleeve of the combustion chamber of the gas turbine, is designed into a cambered surface;
one side of the hood, which is far away from the support cylinder, is provided with a through hole; one part of the supporting head is positioned in a space formed between the supporting head and the supporting barrel, and the other part of the supporting head penetrates through the through hole, is positioned outside the hood and is contacted with the impact sleeve of the transition section of the combustion chamber of the gas turbine.
2. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 1, wherein: the supporting head is a supporting column head which is in an inverted T shape.
3. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 2, wherein: the curvature of the cambered surface on the supporting head is smaller than that of the impact sleeve of the transition section of the combustion chamber of the gas turbine.
4. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 1, wherein: the supporting head is spherical; the curvature of the sphere is smaller than that of the impact sleeve of the transition section of the combustion chamber of the gas turbine.
5. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 4, wherein: the upper gasket is a curved gasket, and the curvature of the curved gasket is smaller than that of the support head.
6. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 1, wherein: the supporting cylinder is welded on an outer ring of an inner layer inlet section of a transition section of the combustion chamber of the gas turbine.
7. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 1, wherein: the hood is sleeved at the upper end of the supporting cylinder in a threaded connection mode.
8. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 7, wherein: the part of the supporting cylinder connected with the hood is provided with an external thread; the part of the hood, which is connected with the support cylinder, is provided with internal threads; the external thread on the supporting cylinder is matched with the internal thread on the hood.
9. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 1, wherein: the outer diameter of the lower gasket is equal to the inner diameter of the support cylinder.
10. The support apparatus for a gas turbine combustor transition piece impingement sleeve of claim 9, wherein: the outer diameter of the upper gasket is smaller than that of the lower gasket.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020393827.4U CN212157263U (en) | 2020-03-25 | 2020-03-25 | Supporting device for gas turbine combustion chamber transition section impact sleeve |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020393827.4U CN212157263U (en) | 2020-03-25 | 2020-03-25 | Supporting device for gas turbine combustion chamber transition section impact sleeve |
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| CN212157263U true CN212157263U (en) | 2020-12-15 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN202020393827.4U Active CN212157263U (en) | 2020-03-25 | 2020-03-25 | Supporting device for gas turbine combustion chamber transition section impact sleeve |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526175A (en) * | 2022-04-24 | 2022-05-24 | 中国航发四川燃气涡轮研究院 | Gear-driven rear duct ejector for afterburner |
| CN115507393A (en) * | 2022-09-20 | 2022-12-23 | 中国联合重型燃气轮机技术有限公司 | Cylinder support, gas turbine combustion chamber and gas turbine |
| CN117366628A (en) * | 2023-10-10 | 2024-01-09 | 中国航发燃气轮机有限公司 | Tube-separating type combustion chamber |
-
2020
- 2020-03-25 CN CN202020393827.4U patent/CN212157263U/en active Active
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114526175A (en) * | 2022-04-24 | 2022-05-24 | 中国航发四川燃气涡轮研究院 | Gear-driven rear duct ejector for afterburner |
| CN115507393A (en) * | 2022-09-20 | 2022-12-23 | 中国联合重型燃气轮机技术有限公司 | Cylinder support, gas turbine combustion chamber and gas turbine |
| CN117366628A (en) * | 2023-10-10 | 2024-01-09 | 中国航发燃气轮机有限公司 | Tube-separating type combustion chamber |
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Address after: 310022 No. 357 Shiqiao Road, Zhejiang, Hangzhou Patentee after: Hangzhou Steam Turbine Holding Co.,Ltd. Address before: 310022 No. 357 Shiqiao Road, Zhejiang, Hangzhou Patentee before: HANGZHOU TURBINE POWER GROUP CO.,LTD. |