CN104196637A - Novel air seal for combustion gas turbine tail barrel and manufacturing method for novel air seal - Google Patents
Novel air seal for combustion gas turbine tail barrel and manufacturing method for novel air seal Download PDFInfo
- Publication number
- CN104196637A CN104196637A CN201410405185.4A CN201410405185A CN104196637A CN 104196637 A CN104196637 A CN 104196637A CN 201410405185 A CN201410405185 A CN 201410405185A CN 104196637 A CN104196637 A CN 104196637A
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- Prior art keywords
- brush
- gas turbine
- air seal
- tail pipe
- seal body
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a novel air seal for a combustion gas turbine tail barrel and a manufacturing method for the novel air seal. The air seal comprises a brush and a sealing piece body, wherein the brush comprises a brush wire cluster and two metal strips; the brush wire cluster is arranged between the two metal strips, so as to form a T shape; the sealing piece body is provided with a brush wire matching surface; the brush wire cluster of the brush is fixed on the brush wire matching surface; the metal strips are clung to the side surfaces of the brush wire matching surface; the brush and the sealing piece body are fixed by welding fixing points. According to the novel air seal, high-temperature gas at an outlet part of the combustion gas turbine tail barrel can be effectively sealed, the problem of sealing failure caused by severe factors such as high-temperature fuel gas can be well controlled by reasonably selecting a material and a processing process. The novel air seal comprises the brush and the sealing piece body, and can resist the oxidation and corrosion caused by the high-temperature gas of a combustion gas turbine. According to the novel air seal and the manufacturing method of the novel air seal, the processing is easy, the control is easy to implement, the rate of finished products is high, and the aims of saving energy and reducing the consumption can be realized.
Description
Technical field
The present invention relates to a kind of gas turbine tail pipe sealing gland and manufacture method thereof, belong to water-tight equipment technical field.
Background technique
In gas turbine operation process, high-temperature fuel gas is through tail pipe, enter before turbine stator blade, need special sealing configuration, prevent that high-temperature gas from leaking, and the brush sealing gland of tail pipe (or being called tail pipe Sealing), can bear the oxide etch of high-temperature fuel gas, can between the assembly being out of shape because of thermal stress, keep again sealing preferably, depend on the outstanding performance of high-performance brush silk, and the rationality in design of Sealing Structure, can meet the seal request of unit.
The brush sealing gland of tail pipe, by resistant to elevated temperatures bulk material, brush, formed, form contact seal with sealed working face, by sealing layer fine and close and that whippy brush silk forms, during high-temperature gas process brush silk, produce flow-disturbing, because brush silk is very thin and fine and close, gas flow resistance is large, thereby leakage rate significantly reduces; Under brush silk high temperature, there is better elasticity simultaneously, can make up the gap because of thermal stress or generation of vibration, remain contact sealing, played good sealing effect.
Conventional gas turbine is monolithic construction by brush sealing gland, and middle operation is made mistakes and can be caused integral body to be scrapped, and loses larger.
Gas turbine belongs to easily damaged parts by brush sealing gland, needs periodic replacement.
Summary of the invention
The object of the present invention is to provide brush sealing gland and manufacture method thereof for a kind of gas turbine, can carry out effective sealing to high-temperature gas, reduce high-temperature gas and leak.
Technical characteristics of the present invention is as follows:
A gas turbine tail pipe sealing gland, described tail pipe sealing gland comprises brush and seal body, and described brush forms with two metal bars by brushing silk bunch, and described brush silk bunch is " T " font in the middle of being arranged on two metal bars; Brush silk fitting surface is set in described seal body, and the brush silk bunch of described brush is fixed on brush silk fitting surface, and described metal bar is close to the side of brush silk fitting surface, by being welded and fixed, a little makes brush and seal body fix.
Above-mentioned metal bar is random geometry.
Cooling pore is set in above-mentioned seal body.
In above-mentioned seal body, spacing hole is set.
A manufacture method for gas turbine tail pipe sealing gland, comprises the steps:
(1), prepare metal bar;
(2), preparation brush silk bunch;
(3), prepare brush;
(4), preparation seal body;
(5), assembling brush envelope;
(6), brush envelope moulding.
In above-mentioned steps (3), a brush silk bunch correspondence is placed in the middle of two metal bars and by end face alignment, brush silk is fixed with metal bar, processing mode is welding.
In above-mentioned steps (5), brush is assemblied on seal body surface of contact, radially, justify align, is fixed.
Above-mentioned steps is fixed into one by brush and seal body in (6), and processing method is for welding, riveted joint, by face of weld polishing, polishing, cleaning.
The beneficial effect that the present invention reaches:
The present invention can effectively seal the high-temperature gas of gas turbine tail pipe (or being called changeover portion) exit portion, by rational material, selects and processing technology, has well controlled the seal failure problem that the severe factors such as high-temperature fuel gas cause; The present invention is comprised of brush, seal body, the oxidation of the machine of resistance to combustion high-temperature gas and corrosion.The present invention processes simply, is easy to control, and yield rate is high, has played energy-saving and cost-reducing object.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the schematic diagram of brush in Fig. 1.
Fig. 3 is the schematic diagram of brush envelope in Fig. 1.
Embodiment
Below in conjunction with accompanying drawing, the invention will be further described.Following examples are only for technological scheme of the present invention is more clearly described, and can not limit the scope of the invention with this.
As shown in Figure 1, Figure 2, Figure 3 shows, a kind of gas turbine tail pipe sealing gland, tail pipe sealing gland comprises brush 3 and seal body 1, and brush 3 is comprised of brush silk bunch 7 and two metal bars 8, and brush silk bunches 7 is arranged on middle " T " font that is of two metal bars 8; A brush silk fitting surface 5 is set in seal body 1, and the brush silk of brush 3 bunches 7 is fixed on brush silk fitting surface 5, and metal bar 8 is close to the side of brush silk fitting surface 5, by being welded and fixed a little, 2 brush 3 and seal body 1 is fixed.
Above-mentioned metal bar 8 is random geometries.
Cooling pore 6 is set in above-mentioned seal body 1.
In above-mentioned seal body 1, spacing hole 4 is set.
A manufacture method for gas turbine tail pipe sealing gland, comprises the steps:
(1), prepare metal bar;
Metal bar can be random geometry, and typical structure is straight line type, circular arc etc.; Metal bar cross section typical structure is square or with the polygonal of chamfering
(2), preparation brush silk bunch;
Preparation brush silk bunch, adopts the method for machining to intercept into fixed length brush silk, by radical requirement, makes brush silk bunch.Brush wire material consists of high temperature resistant material, and material is B alloy wire, mineral salt silk, organic material silk etc.
(3), prepare brush;
A brush silk bunch correspondence is placed in the middle of two metal bars and by end face alignment, brush silk is fixed with metal bar, processing mode is for welding.The brush filament length degree of brush, is greater than seal body and the width of brushing silk mating face
(4), preparation seal body;
Adopt the mode of machining, body blank is processed, according to sealing configuration needs, body member can be random geometry, and structure is straight line type, circular arc etc.
(5), assembling brush envelope;
Brush is assemblied on seal body surface of contact, radially, justify align, is fixed.The brush envelope assembling, brush metal bar and Sealing are connected and fixed a little should keep close contact as much as possible, contact gap 0-0.5mm.
(6), brush envelope moulding.
Brush and seal body are fixed into one, and processing method is welding, riveted joint.By face of weld polishing, polishing, cleaning.Obtain a complete combustion tail cylinder brush envelope.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, do not departing under the prerequisite of the technology of the present invention principle; can also make some improvement and distortion, these improvement and distortion also should be considered as protection scope of the present invention.
Claims (8)
1. a gas turbine tail pipe sealing gland, is characterized in that: described tail pipe sealing gland comprises brush and seal body, and described brush forms with two metal bars by brushing silk bunch, and described brush silk bunch is " T " font in the middle of being arranged on two metal bars; Brush silk fitting surface is set in described seal body, and the brush silk bunch of described brush is fixed on brush silk fitting surface, and described metal bar is close to the side of brush silk fitting surface, by being welded and fixed, a little makes brush and seal body fix.
2. a kind of gas turbine tail pipe sealing gland according to claim 1, is characterized in that: described metal bar is random geometry.
3. a kind of gas turbine tail pipe sealing gland according to claim 1, is characterized in that: cooling pore is set in described seal body.
4. a kind of gas turbine tail pipe sealing gland according to claim 1, is characterized in that: in described seal body, spacing hole is set.
5. a manufacture method for gas turbine tail pipe sealing gland, is characterized in that comprising the steps:
(1), prepare metal bar;
(2), preparation brush silk bunch;
(3), prepare brush;
(4), preparation seal body;
(5), assembling brush envelope;
(6), brush envelope moulding.
6. the manufacture method of a kind of gas turbine tail pipe sealing gland according to claim 5, it is characterized in that: in described step (3), a brush silk bunch correspondence is placed in the middle of two metal bars and end face is alignd, brush silk is fixed with metal bar, and processing mode is welding.
7. the manufacture method of a kind of gas turbine tail pipe sealing gland according to claim 5, is characterized in that: in described step (5), brush is assemblied on seal body surface of contact, radially, justify align, is fixed.
8. the manufacture method of a kind of gas turbine tail pipe sealing gland according to claim 5, is characterized in that: described step is fixed into one by brush and seal body in (6), and processing method is for welding, riveted joint, by face of weld polishing, polishing, cleaning.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410405185.4A CN104196637A (en) | 2014-08-15 | 2014-08-15 | Novel air seal for combustion gas turbine tail barrel and manufacturing method for novel air seal |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410405185.4A CN104196637A (en) | 2014-08-15 | 2014-08-15 | Novel air seal for combustion gas turbine tail barrel and manufacturing method for novel air seal |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104196637A true CN104196637A (en) | 2014-12-10 |
Family
ID=52081981
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410405185.4A Pending CN104196637A (en) | 2014-08-15 | 2014-08-15 | Novel air seal for combustion gas turbine tail barrel and manufacturing method for novel air seal |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN104196637A (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106121739A (en) * | 2016-08-11 | 2016-11-16 | 广东惠州天然气发电有限公司 | A kind of tail pipe sealing member |
| CN106761960A (en) * | 2017-03-21 | 2017-05-31 | 江苏透平电力技术有限公司 | A kind of industrial gas turbine tail pipe brush sealing gland and its manufacture method |
| CN107965391A (en) * | 2017-11-23 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of seal structure between the quiet rotor of aero-engine |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6751962B1 (en) * | 1999-03-08 | 2004-06-22 | Mitsubishi Heavy Industries, Ltd. | Tail tube seal structure of combustor and a gas turbine using the same structure |
| US20090288422A1 (en) * | 2008-05-26 | 2009-11-26 | Christoph Cernay | Component arrangement, combustion chamber arrangement and gas turbine |
| CN102296994A (en) * | 2011-08-03 | 2011-12-28 | 上海电气电站设备有限公司 | Manufacturing technique for brush type steam seal for steam turbines |
| US20130043658A1 (en) * | 2011-08-15 | 2013-02-21 | General Electric Company | Brush seal with backing plate tooth |
| US20130062834A1 (en) * | 2011-09-13 | 2013-03-14 | Rolls-Royce Plc | Brush seal |
| CN103104297A (en) * | 2013-02-05 | 2013-05-15 | 江苏透平密封高科技有限公司 | Brush type seal |
| CN204099062U (en) * | 2014-08-15 | 2015-01-14 | 江苏透平密封高科技有限公司 | A kind of gas turbine tail pipe sealing gland |
-
2014
- 2014-08-15 CN CN201410405185.4A patent/CN104196637A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US6751962B1 (en) * | 1999-03-08 | 2004-06-22 | Mitsubishi Heavy Industries, Ltd. | Tail tube seal structure of combustor and a gas turbine using the same structure |
| US20090288422A1 (en) * | 2008-05-26 | 2009-11-26 | Christoph Cernay | Component arrangement, combustion chamber arrangement and gas turbine |
| CN102296994A (en) * | 2011-08-03 | 2011-12-28 | 上海电气电站设备有限公司 | Manufacturing technique for brush type steam seal for steam turbines |
| US20130043658A1 (en) * | 2011-08-15 | 2013-02-21 | General Electric Company | Brush seal with backing plate tooth |
| US20130062834A1 (en) * | 2011-09-13 | 2013-03-14 | Rolls-Royce Plc | Brush seal |
| CN103104297A (en) * | 2013-02-05 | 2013-05-15 | 江苏透平密封高科技有限公司 | Brush type seal |
| CN204099062U (en) * | 2014-08-15 | 2015-01-14 | 江苏透平密封高科技有限公司 | A kind of gas turbine tail pipe sealing gland |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106121739A (en) * | 2016-08-11 | 2016-11-16 | 广东惠州天然气发电有限公司 | A kind of tail pipe sealing member |
| CN106761960A (en) * | 2017-03-21 | 2017-05-31 | 江苏透平电力技术有限公司 | A kind of industrial gas turbine tail pipe brush sealing gland and its manufacture method |
| CN107965391A (en) * | 2017-11-23 | 2018-04-27 | 中国航发沈阳黎明航空发动机有限责任公司 | A kind of seal structure between the quiet rotor of aero-engine |
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| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C53 | Correction of patent of invention or patent application | ||
| CB02 | Change of applicant information |
Address after: 210046, Nanjing, Qixia District, Jiangsu Province, Gan home East 108, Nanjing Golden Port (state) science and Technology Park 6 Applicant after: Jiangsu Turbine Seal High-Technology Co., Ltd. Address before: 210046, Nanjing, Qixia District, Jiangsu Province, Gan home East 108, Nanjing Golden Port (state) science and Technology Park 6 Applicant before: Jiangsu Turbine Seal High-Technology Co., Ltd. |
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| COR | Change of bibliographic data |
Free format text: CORRECT: APPLICANT; FROM: JIANGSU TURBINE SEAL HIGH-TECHNOLOGY CO., LTD. TO: JIANGSU TURBINE SEAL HIGH-TECHNOLOGY CO., LTD. |
|
| C53 | Correction of patent of invention or patent application | ||
| CB03 | Change of inventor or designer information |
Inventor after: Zou Yi Inventor after: Zuo Fei Inventor after: Shen Xiannian Inventor after: Gu Wenwu Inventor before: Zou Yi Inventor before: Shen Xiannian Inventor before: Gu Wenwu |
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| COR | Change of bibliographic data |
Free format text: CORRECT: INVENTOR; FROM: ZOU YI SHEN XIANNIAN GU WENWU TO: ZOU YI ZUO FEI SHEN XIANNIAN GU WENWU |
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| RJ01 | Rejection of invention patent application after publication | ||
| RJ01 | Rejection of invention patent application after publication |
Application publication date: 20141210 |