CN104896514A - Anti-vibration heat insulation wall of main combustion chamber of gas turbine - Google Patents
Anti-vibration heat insulation wall of main combustion chamber of gas turbine Download PDFInfo
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- CN104896514A CN104896514A CN201510240113.3A CN201510240113A CN104896514A CN 104896514 A CN104896514 A CN 104896514A CN 201510240113 A CN201510240113 A CN 201510240113A CN 104896514 A CN104896514 A CN 104896514A
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Abstract
An anti-vibration heat insulation wall of a main combustion chamber of a gas turbine comprises an inner wall and an outer wall, and the inner wall is uneven and is fixed to the outer wall; a communication cavity is formed between the outer wall and the inner wall; a plurality of film holes are formed in the inner wall, and are communicated with the cavity; positions, close to the center of the combustion chamber, of the film holes are sparsely distributed, and the positions, close to the outer wall, of the film holes are densely distributed; and the anti-vibration heat insulation wall of the main combustion chamber of the gas turbine is simple in structure, an air path is convenient to mount, the film holes are easily arranged, and the wall has the wide application prospect. The structure of the wall face of the main combustion chamber is changed, transmission of sound waves in the main combustion chamber is changed, and therefore the phase difference between sound pressure vibration and heat release speed fluctuation cannot be kept unchangeable always, so that vibrating burning is prevented from happening; and the film holes are formed, on the one hand, vibration energy of pressure pulses can be absorbed, and on the other hand, thermal erosion of gas to the combustion chamber wall can be prevented, so that the service life of an engine can be prolonged.
Description
Technical field
The invention belongs to gas-turbine unit technical field, be specifically related to the wall of gas turbine main chamber, be i.e. the barrel of burner inner liner.
Background technology
Gas turbine is the crystallization of modern industry achievement, and combustion chamber is the vitals of gas turbine, and the major function of combustion chamber makes the chemical energy of fuel be heat energy.Combustion chamber, in the process of fuel combustion, often can produce some problems, as oscilatory occurrence.When hugging occurs, the significantly vibration of the adjoint thermal discharge of meeting and pressure, produces huge noise, causes burner high vibration, affect the normal work of burner, even can cause the damage and failure of system unit time serious.In general, when disturbance reach that chemical reaction releases energy 0.1% time, the amplitude of the pressure fluctuation produced just is equivalent to combustion chamber average pressure peak amplitude.This significantly pressure fluctuation is easy to the heavy damage causing structure.
In the combustion process of gas-turbine combustion chamber, due to the interaction that fuel combustion heat liberation rate, heat release rate and acoustic pressure fluctuate, there will be hot acoustic instability phenomenon, it shows as pressure vibration and increases, and produces noise, may destroy the structure of combustion chamber time serious.The generation of hugging has a huge impact the operation of Actual combustion room and security.Hugging can cause combustion chambers burn stability to decline, and by directly causing stopping working time serious, has disastrous effect to combustion chamber.Hugging makes combustion position worsen, and the pressure fluctuation that hugging causes likely destroys the structure of combustion chamber.Therefore, constantly carry out the research about hugging both at home and abroad, on the study mechanism of hugging, had many progress now, but in the prevention of gas turbine main chamber hugging, do not occur more satisfactory scheme temporarily.
In combustion system, unstable Thermal release transferring energy, to sound field, might not cause combustion instability.When oscillation of sound pressure differs 0 ~ 90 degree with rate of heat release wave phase, when only having periodic Thermal release process to provide the speed of energy faster than the speed of sound wave by the energy of the decay of the border of combustion chamber and diffusion to sound field, combustion process just becomes instability.
Low-frequency oscillation burning in combustion chamber is normally fluctuated by fuel in combustion chamber combustion heat release rate and acoustic pressure and is intercoupled, and generation self-oscillation causes.Its general mechanism is: if combustion heat release speed has a small change, this small change can produce acoustic pressure disturbance, and sound wave, in burning indoor propagation, returns after running into wall, affect again fuel supply rate conversely, thus combustion heat release rate is changed again.Namely combustion heat release and pressure oscillation influence each other, and when the appropriate phase mutual excitation of phase place, form positive feedback loop.Modern gas turbine generally all requires high temperature rise, and high temperature rise makes term durability gas turbine flame barrel overheated, so combustion chamber wall surface generally all can take certain cooling provision.Modern gas turbine combustion chamber face portion takes floating wall-like structure to cool, part takes maze-type structure to cool, although these two kinds of types of cooling can obtain good cooling effect, combustion chamber wall surface structure all relative complex of this constructed in two ways, difficulty of processing is large.
Summary of the invention
Technical problem to be solved by this invention is to provide a kind of gas turbine main chamber vibrationproof thermal wall, and the heat insulation wall energy of this vibrationproof effectively prevents the generation of oscilatory occurrence in gas turbine main chamber, and can improve its cooling effectiveness.
It is as follows that the present invention solves the problems of the technologies described above the technical scheme taked: a kind of gas turbine main chamber vibrationproof thermal wall, described vibrationproof thermal wall comprises inner and outer wall, described inwall is uneven, and described inwall is fixed on described outer wall, forms the cavity of connection between two walls.
Vibrationproof thermal wall of the present invention has double-decker, the cavity of connection is formed between two walls, be convenient to pass into cold air cooling, there is comparatively high cooling efficiency, the present invention is by rough inwall, change the reflections propagate of sound wave in combustion chamber, thus make the phase difference that oscillation of sound pressure and HRR fluctuate can not remain constant, and then prevent the appearance of hugging.
As improvement of the present invention: described inwall is provided with multiple air film hole, described air film hole is communicated with described cavity.Cold air flows out from air film hole, inner surface place at inwall is formed one deck air film, and this air film can reside in the recess of inwall inner surface relatively stablely, effectively prevent the hot erosion of combustion gas to chamber wall, meanwhile, air film hole also helps the oscillation energy of absorption pressure pulsation.
As the preferred embodiment of the present invention: described air film hole is more sparse in the position distribution near center, combustion chamber, at the comparatively dense that distributes near outer wall position.The many perforates of raised position, the few perforate of recessed position, can improve cooling effectiveness in the situation that tolerance is constant.
As recommendation embodiment of the present invention: described inwall is corrugated plating, described air film hole is at the crest location comparatively dense of corrugated plating, more sparse in its wave trough position.
Described corrugated plating is in sinusoidal or cosine wave structure, and the cambered surface being semi-circular structure by multiple cross section is spliced.
The radius change scope of described semicircle is between 10mm ~ 40mm, distance between main chamber inwall centre position and outer wall is 10 ~ 50mm, between corrugated plating crest and trough, air film hole sets in a row, there are 3 ~ 12 rows, often be vented the spacing of fenestra between 2 times of air film hole diameters to 10 times of air film hole diameters, air film hole pore diameter range is 0.5mm ~ 5mm.
Relative to prior art, the present invention has following beneficial effect:
1) gas turbine main chamber vibrationproof thermal-insulated wall construction of the present invention is simple, and gas circuit arranges also very convenient, and the setting of air film hole is also relatively easy, has broad application prospects;
2) the present invention is by changing the structure of main chamber wall, changes the propagation of sound wave in main chamber, and then makes the phase difference that oscillation of sound pressure and HRR fluctuate can not remain constant, thus prevent the generation of hugging; The present invention arranges air film hole, on the one hand can the oscillation energy of absorption pressure pulsation, can combustion gas can be prevented the hot erosion of chamber wall on the one hand, be conducive to the service life of improving engine.
Accompanying drawing explanation
Fig. 1 is the sectional view (cross section) of the gas turbine main chamber vibrationproof thermal wall of present pre-ferred embodiments;
Fig. 2 is the arrangement architecture schematic diagram of air film hole on corrugated plating;
Fig. 3 is the enlarged drawing at a place in Fig. 2.
Detailed description of the invention
As shown in Figure 1, 2, the gas turbine main chamber vibrationproof thermal wall of the present embodiment comprises inwall 1 and outer wall 2, and in this embodiment, inwall 1 is rough corrugated plating, and inwall 1 is fixed on outer wall 2, forms the cavity 3 of connection between two walls.Inwall 1 is provided with multiple air film hole 11, air film hole 11 is communicated with cavity 3, as shown in Figure 2.Air film hole 11 punish cloth near the crest location 12 at center, combustion chamber more sparse, to distribute comparatively dense in the wave trough position 13 near outer wall 2.
Corrugated plating is in sinusoidal or cosine wave structure, and the cambered surface being semi-circular structure by multiple cross section is spliced.This corrugated plating can for having the corrugated plating of longitudinal ripple, also can for having the corrugated plating of transverse wave, and in Fig. 1, corrugated plating is the corrugated plating with transverse wave.
The radius change scope of the semicircle of the cambered surface of above-mentioned semi-circular structure is between 10mm ~ 40mm.The distance in main chamber outer wall and inwall centre position is 10 ~ 50mm.Between corrugated plating crest 12 and trough 13, air film hole 11 sets in a row, and total row is between 3 ~ 12 rows, and often the centre-to-centre spacing d of exhaust fenestra 11 is at 2 times of air film hole diameters to 10 times of air film hole diameters, and air film hole 11 pore diameter range is 0.5mm ~ 5mm, as shown in Figure 3.
Corrugated board structures of the present invention has obvious enhanced heat exchange effect, and the runner fluctuation that corrugated board structures brings produces turbulence prediction better can increase heat convection.As shown in Figure 2, on corrugated plating, air film hole can be given vent to anger by dynamic pressure and be strengthened overflow heat exchange, the many perforates in crest place, the few perforate in trough place, can improve cooling effectiveness in the situation that tolerance is constant.
Inwall at corrugated plating is formed one deck air film by the cold air flowed out from the air film hole corrugated plating, this air film can reside in the trough of corrugated plating relatively stablely, effectively prevent the hot erosion of combustion gas to chamber wall, thus be conducive to the service life of improving engine.
Claims (6)
1. a gas turbine main chamber vibrationproof thermal wall, is characterized in that, described vibrationproof thermal wall comprises inner and outer wall, and described inwall is uneven, and described inwall is fixed on described outer wall, forms the cavity of connection between two walls.
2. gas turbine main chamber vibrationproof thermal wall according to claim 1, it is characterized in that, described inwall is provided with multiple air film hole, and described air film hole is communicated with described cavity.
3. gas turbine main chamber vibrationproof thermal wall according to claim 2, is characterized in that, described air film hole is more sparse in the position distribution near center, combustion chamber, at the comparatively dense that distributes near outer wall position.
4. gas turbine main chamber vibrationproof thermal wall according to claim 3, it is characterized in that, described inwall is corrugated plating, and described air film hole is at the crest location comparatively dense of corrugated plating, more sparse in its wave trough position.
5. gas turbine main chamber vibrationproof thermal wall according to claim 4, is characterized in that, described corrugated plating is in sinusoidal or cosine wave structure, and the cambered surface being semi-circular structure by multiple cross section is spliced.
6. gas turbine main chamber vibrationproof thermal wall according to claim 5, it is characterized in that, the radius change scope of described semicircle is between 10mm ~ 40mm, distance between main chamber inwall centre position and outer wall is 10 ~ 50mm, between corrugated plating crest and trough, air film hole sets in a row, have 3 ~ 12 rows, be often vented the spacing of fenestra between 2 times of air film hole diameters to 10 times of air film hole diameters, air film hole pore diameter range is 0.5mm ~ 5mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201510240113.3A CN104896514A (en) | 2015-05-13 | 2015-05-13 | Anti-vibration heat insulation wall of main combustion chamber of gas turbine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201510240113.3A CN104896514A (en) | 2015-05-13 | 2015-05-13 | Anti-vibration heat insulation wall of main combustion chamber of gas turbine |
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| CN104896514A true CN104896514A (en) | 2015-09-09 |
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| CN201510240113.3A Pending CN104896514A (en) | 2015-05-13 | 2015-05-13 | Anti-vibration heat insulation wall of main combustion chamber of gas turbine |
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105605605A (en) * | 2016-01-25 | 2016-05-25 | 西北工业大学 | Anti-vibration cooling wall of ground gas turbine combustion chamber |
| CN107289620A (en) * | 2017-07-17 | 2017-10-24 | 浙江天翔环保设备有限公司 | A kind of anti-scald and the boiler of environmental protection |
| CN107328094A (en) * | 2017-07-17 | 2017-11-07 | 浙江天翔环保设备有限公司 | A kind of boiler of easy cleaning carbon slag |
| CN109519284A (en) * | 2018-12-12 | 2019-03-26 | 北京动力机械研究所 | A kind of combustion chamber heat screen |
| CN109595591A (en) * | 2018-12-03 | 2019-04-09 | 西北工业大学 | A kind of corrugated plating heat screen with water cooling curtain wall |
| CN109707533A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type injection cooling structure |
| CN109707532A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type active cooling structure |
| CN109779782A (en) * | 2019-03-08 | 2019-05-21 | 西北工业大学 | The double wall cooling structure with longitudinal ripple impact orifice plate for vector spray |
| CN112923398A (en) * | 2021-03-04 | 2021-06-08 | 西北工业大学 | Afterburning chamber antivibration heat screen |
| CN113551260A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | V-shaped flame stabilizer with flow guide holes |
| CN115704563A (en) * | 2021-08-13 | 2023-02-17 | 北京航空航天大学 | Combustion chamber and combustor |
Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3837411A (en) * | 1973-11-21 | 1974-09-24 | Gen Electric | Diverter valve for a gas turbine with an augmenter |
| CN86105250A (en) * | 1986-08-07 | 1988-02-17 | 通用电气公司 | Impingement cooled transition duct |
| CN1052730A (en) * | 1989-12-22 | 1991-07-03 | 株式会社日立制作所 | Combustion method in combustion apparatus and this kind equipment |
| EP0486133A1 (en) * | 1990-11-15 | 1992-05-20 | General Electric Company | Film cooled combustor liner for gas turbine |
| CN1450304A (en) * | 2002-04-10 | 2003-10-22 | 通用电气公司 | Annular one-piece corrugated liner for combustor of gas turbine engine |
| US20040211188A1 (en) * | 2003-04-28 | 2004-10-28 | Hisham Alkabie | Noise reducing combustor |
| CN1551965A (en) * | 2001-09-07 | 2004-12-01 | ��ķ�Ƽ���������˾ | Damping arrangement for reducing combustion chamber pulsations in a gas turbine system |
| CN1580640A (en) * | 2003-07-31 | 2005-02-16 | 联合工艺公司 | Combustor |
| CN102072488A (en) * | 2011-01-31 | 2011-05-25 | 哈尔滨工业大学 | High speed burner for combustion chamber with film cooling type corrugated shell structure |
| CN103534531A (en) * | 2011-03-31 | 2014-01-22 | 株式会社Ihi | Combustor for gas turbine engine and gas turbine |
| CN203671657U (en) * | 2013-12-10 | 2014-06-25 | 中航商用航空发动机有限责任公司 | Flame tube and gas turbine combustion chamber comprising same |
| CN103968418A (en) * | 2014-05-26 | 2014-08-06 | 西北工业大学 | Double-layer-wall heat insulation screen used for afterburner |
| CN104033927A (en) * | 2014-06-12 | 2014-09-10 | 中国航空动力机械研究所 | Combustion chamber based on RQL principle and aircraft engine with same |
| CN204227467U (en) * | 2014-10-28 | 2015-03-25 | 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 flame combustion chamber barrel structure |
-
2015
- 2015-05-13 CN CN201510240113.3A patent/CN104896514A/en active Pending
Patent Citations (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US3837411A (en) * | 1973-11-21 | 1974-09-24 | Gen Electric | Diverter valve for a gas turbine with an augmenter |
| CN86105250A (en) * | 1986-08-07 | 1988-02-17 | 通用电气公司 | Impingement cooled transition duct |
| CN1052730A (en) * | 1989-12-22 | 1991-07-03 | 株式会社日立制作所 | Combustion method in combustion apparatus and this kind equipment |
| EP0486133A1 (en) * | 1990-11-15 | 1992-05-20 | General Electric Company | Film cooled combustor liner for gas turbine |
| CN1551965A (en) * | 2001-09-07 | 2004-12-01 | ��ķ�Ƽ���������˾ | Damping arrangement for reducing combustion chamber pulsations in a gas turbine system |
| CN1450304A (en) * | 2002-04-10 | 2003-10-22 | 通用电气公司 | Annular one-piece corrugated liner for combustor of gas turbine engine |
| US20040211188A1 (en) * | 2003-04-28 | 2004-10-28 | Hisham Alkabie | Noise reducing combustor |
| CN1580640A (en) * | 2003-07-31 | 2005-02-16 | 联合工艺公司 | Combustor |
| CN102072488A (en) * | 2011-01-31 | 2011-05-25 | 哈尔滨工业大学 | High speed burner for combustion chamber with film cooling type corrugated shell structure |
| CN103534531A (en) * | 2011-03-31 | 2014-01-22 | 株式会社Ihi | Combustor for gas turbine engine and gas turbine |
| CN203671657U (en) * | 2013-12-10 | 2014-06-25 | 中航商用航空发动机有限责任公司 | Flame tube and gas turbine combustion chamber comprising same |
| CN103968418A (en) * | 2014-05-26 | 2014-08-06 | 西北工业大学 | Double-layer-wall heat insulation screen used for afterburner |
| CN104033927A (en) * | 2014-06-12 | 2014-09-10 | 中国航空动力机械研究所 | Combustion chamber based on RQL principle and aircraft engine with same |
| CN204227467U (en) * | 2014-10-28 | 2015-03-25 | 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 flame combustion chamber barrel structure |
Cited By (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105605605A (en) * | 2016-01-25 | 2016-05-25 | 西北工业大学 | Anti-vibration cooling wall of ground gas turbine combustion chamber |
| CN107289620A (en) * | 2017-07-17 | 2017-10-24 | 浙江天翔环保设备有限公司 | A kind of anti-scald and the boiler of environmental protection |
| CN107328094A (en) * | 2017-07-17 | 2017-11-07 | 浙江天翔环保设备有限公司 | A kind of boiler of easy cleaning carbon slag |
| CN107328094B (en) * | 2017-07-17 | 2024-06-04 | 浙江天翔环保设备有限公司 | Boiler convenient for cleaning carbon slag |
| CN107289620B (en) * | 2017-07-17 | 2024-05-24 | 诸暨市海逸针织有限公司 | Scald preventing and environmental protection boiler |
| CN109595591A (en) * | 2018-12-03 | 2019-04-09 | 西北工业大学 | A kind of corrugated plating heat screen with water cooling curtain wall |
| CN109707532A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type active cooling structure |
| CN109707533A (en) * | 2018-12-12 | 2019-05-03 | 中国航空工业集团公司西安飞机设计研究所 | A kind of bridging type injection cooling structure |
| CN109519284A (en) * | 2018-12-12 | 2019-03-26 | 北京动力机械研究所 | A kind of combustion chamber heat screen |
| CN109779782A (en) * | 2019-03-08 | 2019-05-21 | 西北工业大学 | The double wall cooling structure with longitudinal ripple impact orifice plate for vector spray |
| CN112923398A (en) * | 2021-03-04 | 2021-06-08 | 西北工业大学 | Afterburning chamber antivibration heat screen |
| CN112923398B (en) * | 2021-03-04 | 2022-07-22 | 西北工业大学 | Afterburning chamber antivibration heat screen |
| CN113551260A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | V-shaped flame stabilizer with flow guide holes |
| CN115704563A (en) * | 2021-08-13 | 2023-02-17 | 北京航空航天大学 | Combustion chamber and combustor |
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Application publication date: 20150909 |
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