CN204388127U - Natural gas fuel gas turbine toroidal combustion chamber - Google Patents
Natural gas fuel gas turbine toroidal combustion chamber Download PDFInfo
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- CN204388127U CN204388127U CN201420729875.0U CN201420729875U CN204388127U CN 204388127 U CN204388127 U CN 204388127U CN 201420729875 U CN201420729875 U CN 201420729875U CN 204388127 U CN204388127 U CN 204388127U
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- combustion chamber
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- inner casing
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Abstract
The utility model proposes natural gas fuel gas turbine toroidal combustion chamber.Combustion chamber inner casing is made up of symmetrical four parts, every part respectively profit is bolted on high-pressure compressor support case and high-pressure turbine support case, combustion chamber inner casing there are equally distributed 36 installing holes, for connecting 36 premix sections, all with deflector in premix section, respectively there is a nozzle installing hole each premix section front end, and nozzle is arranged in the nozzle installing hole of premix section front end respectively; Diffuser is connected respectively by group section with premix section, and each group section is all with main air inlet, cooling air intake, combustion air inlet, cooling-air outlet and high-temperature fuel gas passage; Combustion chamber inner casing, combustor outer casing, high-pressure compressor support case, between high-pressure turbine support case and group section formed cooling endless belt.Ensure gas-turbine combustion chamber stable work in work, and easily divide de-assembly, be convenient to the maintenance after gas-turbine combustion chamber use and maintenance.
Description
technical field:
The utility model relates to Thermal Energy and Power Engineering control field, specifically a kind of natural gas fuel gas turbine toroidal combustion chamber.
background technology:
Gas turbine is since last century, early forties came out, there is because of it series of advantages such as power is large, efficiency is high, volume is little, starting is fast, smooth running, manipulation is simple, maintaining is convenient, reliable operation, in short over half a century, achieved the development of advancing by leaps and bounds, the numerous areas such as the electric power in countries in the world, petrochemical industry, traffic, metallurgy, military affairs obtains increasingly extensive application.The height of gas turbine technology level has now become one of important symbol of a national science and technology level and military strength.
Toroidal combustion chamber has the series of advantages such as volume is little, lightweight, flow resistance loss is little, connection flame is convenient, smoking of the exhaust heating surface area that is few, burner inner liner is little, development potentiality is large, is a kind of rising structural shape.Its suitable especially and axial-flow compressor cooperating.But because combustion space is linked up each other, air-flow and burning torch are just not easily organized, combustibility is more restive, the impact that gas outlet temperature field is subject to inlet flow field keeps more greatly and not easily stable, air-source simultaneously owing to needing power especially big when making Full scale testing, and the rigidity of structure is poor, and unit is not easy to strip inspection again, cause this combustion chamber once not obtained for a long time to widely use, but among developing rapidly at present.
According to a series of unfavorable factors of above-mentioned toroidal combustion chamber, 2014 Nian Guanghan gas turbine Co., Ltds have carried out a large amount of theories and experimental study, achieve toroidal combustion chamber when combustion space is linked up each other, the superperformances such as low flow resistance loss, flameholding, outlet temperature are even, meanwhile, the feature that toroidal combustion chamber easily decomposes and assembles is also achieved.
utility model content:
The utility model is to solve toroidal combustion chamber air-flow and torch is not easily organized, gas outlet temperature field is subject to inlet flow field the impact of burning is comparatively large, be not easy to the technical problems such as overhaul, provide a kind of flameholding, outlet temperature evenly, the annular firing cell structure of easily point de-assembly, rear local maintenance easy to use and maintenance.
The technical solution of the utility model is: natural gas fuel gas turbine toroidal combustion chamber, comprise combustor outer casing, whole combustor outer casing is bolted on high-pressure compressor support case and high-pressure turbine support case, combustion chamber inner casing is made up of symmetrical four parts, every part respectively profit is bolted on high-pressure compressor support case and high-pressure turbine support case, combustion chamber inner casing there are equally distributed 36 installing holes, for connecting 36 premix sections, all with deflector in 36 premix sections, respectively there is a nozzle installing hole each premix section front end, 36 nozzles are arranged in 36 premix section front end nozzle installing holes respectively, 36 diffusers are connected respectively by 36 group sections with 36 premix sections, and each group section is all with main air inlet, cooling air intake, combustion air inlet, cooling-air outlet and high-temperature fuel gas passage, combustion chamber inner casing, combustor outer casing, high-pressure compressor support case, between high-pressure turbine support case and group section formed cooling endless belt.
Combustor outer casing is made up of symmetrical four parts, and every part utilizes bolt to be fixedly assembled into ring, with seven radiated ribs in every part, combustor outer casing has two installing hole mounting points firearms.
Combustion chamber inner casing inner surface is with heat insulating coat.
The utility model has following beneficial effect: one, combustor outer casing adopts the Split type structure of symmetrical four sections fit Cheng Huan, with radiated rib on it; Split type structure achieves the dismounting to single position, combustion chamber, and does not affect gas turbine remainder; Radiated rib makes combustion chamber wall surface have better heat sinking function, reduces chamber wall surface temperature; Two, combustion chamber inner casing adopts the Split type structure of symmetrical four sections fit Cheng Huan, inner wall belt heat insulating coat, combustion chamber inner casing Split type structure is the dismounting in order to realize single position, combustion chamber equally, and inwall heat insulating coat achieves and reduces combustion chamber inner casing outside wall surface temperature; Three, combustion chamber inner casing, combustor outer casing, high-pressure compressor support case, formed between high-pressure turbine support case and group section and cool endless belt, utilize cooling-air combustor outer casing, high-pressure compressor support case, high-pressure turbine support case and combustion chamber inner casing to be isolated, reduce the surface temperature of combustor outer casing, high-pressure compressor support case and high-pressure turbine support case; Four, nozzle is installed in premix section front end, adopts premix intersegmental part deflector that the combustion gas entered from nozzle is fully mixed with compressed air, ensure that combustor exit temperature is evenly distributed.
accompanying drawing illustrates:
Fig. 1 is structural representation of the present utility model;
Accompanying drawing 2 is the A-A sectional view of accompanying drawing 1;
Accompanying drawing 3 is the structural front view for premix section in the utility model;
Accompanying drawing 4 is the main sectional view of structure of group section in the utility model.
1-combustor outer casing in figure, 2-combustion chamber inner casing, 3-high-pressure compressor support case, 4-premix section, 5-nozzle, 6-high-pressure turbine support case, 7-group section, 8-diffuser, 9-heat insulating coat, 10-cooling-air exports, and 11-cools endless belt, 12-cooling air intake, 13-radiated rib, 14-igniter, 15-nozzle installing hole, 16-deflector, 17-main air inlet, 18-combustion air inlet, 19-cooling duct, 20-high-temperature fuel gas passage.
detailed description of the invention:
Below in conjunction with accompanying drawing, the utility model is described in further detail:
Shown in Fig. 1 composition graphs 2 ~ Fig. 4, natural gas fuel gas turbine toroidal combustion chamber, comprise combustor outer casing 1, whole combustor outer casing 1 is bolted to high-pressure compressor support case 3 with on high-pressure turbine support case 6, combustion chamber inner casing 2 is made up of symmetrical four parts, every part respectively profit is bolted to high-pressure compressor support case 3 with on high-pressure turbine support case 6, combustion chamber inner casing 2 there are equally distributed 36 installing holes, for connecting 36 premix sections 4, all with deflector 16 in 36 premix sections 4, respectively there is a nozzle installing hole 15 each premix section 4 front end, 36 nozzles 5 are arranged in 36 premix section 4 front end nozzle installing holes 15 respectively, 36 diffusers 8 are connected respectively by 36 group sections 7 with 36 premix sections 4, and each group section 7 is all with main air inlet 17, cooling air intake 12, combustion air inlet 18, cooling-air outlet 10 and high-temperature fuel gas passage 20, combustion chamber inner casing 2, combustor outer casing 1, high-pressure compressor support case 3, between high-pressure turbine support case 6 and group section 7 formed cooling endless belt 11.
Combustor outer casing 1 is made up of symmetrical four parts, and every part utilizes bolt to be fixedly assembled into ring, with seven radiated ribs 13 in every part, combustor outer casing 1 has two installing holes, for mounting points firearm 14.
Combustion chamber inner casing 2 inner surface is with heat insulating coat 9.
Cooling-air is entered by the cooling air intake 12 of group section 7, flow through cavity that combustion chamber inner casing 2 formed with high-pressure turbine support case 6 respectively successively, cavity that cavity, combustion chamber inner casing 2 and high-pressure compressor support case 3 that combustion chamber inner casing 2 is formed with combustor outer casing 1 are formed, finally flow into group section 7 cooling duct 19, flow out from cold gas outlet 10.
Claims (3)
1. a natural gas fuel gas turbine toroidal combustion chamber, comprise burning chamber shell (1), it is characterized in that: whole combustor outer casing (1) is bolted to high-pressure compressor support case (3) with on high-pressure turbine support case (6), combustion chamber inner casing (2) is made up of symmetrical four parts, every part respectively profit is bolted to high-pressure compressor support case (3) with on high-pressure turbine support case (6), combustion chamber inner casing (2) there are equally distributed 36 installing holes, for connecting 36 premix sections (4), all with deflector (16) in 36 premix sections (4), respectively there is a nozzle installing hole (15) each premix section (4) front end, 36 nozzles (5) are arranged in 36 premix sections (4) front end nozzle installing hole (15) respectively, 36 diffusers (8) are connected respectively by 36 group sections (7) with 36 premix sections (4), and each group section (7) is all with main air inlet (17), cooling air intake (12), combustion air inlet (18), cooling-air outlet (10) and high-temperature fuel gas passage (20), combustion chamber inner casing (2), combustor outer casing (1), high-pressure compressor support case (3), formation cooling endless belt (11) between high-pressure turbine support case (6) and group section (7).
2. natural gas fuel gas turbine toroidal combustion chamber according to claim 1, it is characterized in that: combustor outer casing (1) is made up of symmetrical four parts, every part utilizes bolt to be fixedly assembled into ring, with seven radiated ribs (13) in every part, combustor outer casing (1) there are two installing hole mounting points firearms (14).
3. natural gas fuel gas turbine toroidal combustion chamber according to claim 1, is characterized in that: combustion chamber inner casing (2) inner surface is with heat insulating coat (9).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420729875.0U CN204388127U (en) | 2014-11-29 | 2014-11-29 | Natural gas fuel gas turbine toroidal combustion chamber |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420729875.0U CN204388127U (en) | 2014-11-29 | 2014-11-29 | Natural gas fuel gas turbine toroidal combustion chamber |
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| Publication Number | Publication Date |
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| CN204388127U true CN204388127U (en) | 2015-06-10 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN201420729875.0U Active CN204388127U (en) | 2014-11-29 | 2014-11-29 | Natural gas fuel gas turbine toroidal combustion chamber |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104807043A (en) * | 2014-11-29 | 2015-07-29 | 哈尔滨广瀚燃气轮机有限公司 | Annular combustion chamber of natural gas fuel gas turbine |
| CN112460633A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing method for combustion chamber of gas turbine |
| CN112460631A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing device for combustion chamber of gas turbine |
-
2014
- 2014-11-29 CN CN201420729875.0U patent/CN204388127U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104807043A (en) * | 2014-11-29 | 2015-07-29 | 哈尔滨广瀚燃气轮机有限公司 | Annular combustion chamber of natural gas fuel gas turbine |
| CN112460633A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing method for combustion chamber of gas turbine |
| CN112460631A (en) * | 2020-10-27 | 2021-03-09 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing device for combustion chamber of gas turbine |
| CN112460631B (en) * | 2020-10-27 | 2022-01-21 | 中国船舶重工集团公司第七0三研究所 | Gas fuel and air mixing device for combustion chamber of gas turbine |
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