CN104295374A - Gas turbine heat regenerator with rotary body layout and heat exchange process thereof - Google Patents
Gas turbine heat regenerator with rotary body layout and heat exchange process thereof Download PDFInfo
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- CN104295374A CN104295374A CN201410445138.2A CN201410445138A CN104295374A CN 104295374 A CN104295374 A CN 104295374A CN 201410445138 A CN201410445138 A CN 201410445138A CN 104295374 A CN104295374 A CN 104295374A
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Abstract
The invention relates to a gas turbine heat regenerator with a rotary body layout and a heat exchange process thereof. The gas turbine heat regenerator includes a housing (1), which is internally provided with a heat exchanger (2). The heat exchanger (2) consists of a set of fan shaped heat exchange core bodies (21), the heat exchange core bodies (21) are circumferentially arranged to form a ring body and independent to each other. Fixation support arms (22) and floating support arms (23) are disposed on both sides of the heat exchange core bodies (21). The high temperature flue gas and high pressure gas formed in the heat exchanger (2) form countercurrent channels. Through the rotary body layout, the gas turbine heat regenerator provided by the invention integrates over ten heat regenerator core bodies to increase the heat dissipation capability. A countercurrent mode is employ to arrange the flow channel of flue gas and compressed air so as to make the heat dissipation efficiency reach the highest. And according to difference of temperature, pressure and density on the flue gas side and the compressed air side, fin structures with different heights are employed to conduct optimization so as to improve the comprehensive heat dissipation ability of the heat regenerator.
Description
Technical field
The present invention relates to a kind of gas turbine regenerator of solid of rotation layout, belong to technical field of heat exchangers.
Background technique
Gas-turbine power plant, as marine main power plant, has the advantages such as volume is little, lightweight, startup is fast, operation maintenance convenience, subsidiary engine and system are simple.What require for naval vessel propelled at high velocity system main power plant along with shipbuilding circles improves constantly, and the series of advantages such as the unit specific power that gas turbine has is large, size is little, lightweight, gearshift performance good, simple to operate, easy to maintenance, lube use rate is few and noise is little under water seems and becomes increasingly conspicuous.
Intercooled regeneration circulation (ICR-IntercoolingRecuperated) gas turbine is the gas turbine adding the parts such as compressed-air intercooler, exhaust regenerator on simple cycle gas turbine engine basis, its outstanding advantages all has the higher thermal efficiency under design conditions and low operating mode, compensate for the simple cycle gas turbine engine shortcoming that the thermal efficiency is low under low operating mode, thus be that military-civil naval vessel adopts full combustion power plant to create condition.Adopt ICR gas turbine that total road fuel consumption can be made to decline 23 % ~ 25 %, power stage increases by 25% ~ 30%.
Regenerator, as the critical component of ICR cycle combustion turbine, its operating conditions, more complicated: gas utensil is corrosive, needs the high temperature bearing more than 950K, the temperature difference of 400K, and the pressure of tens air is born in its inside.Gas turbine regenerator belongs to gas-gas-heat exchanger, and the coefficient of heat transfer of gas is smaller, and for reaching certain heat exchange efficiency, the volume of regenerator likely becomes very huge.Therefore, to the topology layout of gas turbine regenerator, become extremely important.
The regenerator design and manufaction of gas turbine, has three large difficult points: 1. heat dissipating capacity is comparatively large, particularly large ship gas turbine, and the heat dissipating capacity of regenerator reaches 2-3 ten thousand kilowatts, even higher; 2. combustion gas and compressed-air actuated flow resistance little, generally only have about 5% of pressure itself, particularly the flow resistance of combustion gas side, tightly only allow at about 5kPa; 3. greatly, the reliability requirement of regenerator is high for heat load, thermal expansion, thermal shock.Meanwhile, regenerator also has a feature, and the inlet pressure of combustion gas is little, and close to normal atmosphere (An), seal request is not high, allows a small amount of leakage.
Summary of the invention
The present invention is directed to above-mentioned defect, object is to provide gas turbine regenerator and the heat transfer process thereof of a kind of solid of rotation layout that a kind of structure is simple, heat-exchange performance is good.
The technical solution used in the present invention is for this reason: the present invention includes housing (1), is provided with heat exchanger (2) in housing (1); Described heat exchanger (2) is made up of (21) the heat exchange core that a group is fan shape, each heat exchange core (21) hoop arranges formation one annular solid, each heat exchange core (21) is separate, establishes fixed support arm (22) and float support arm (23) in heat exchange core (21) both sides; Heat exchanger (2) formed high-temperature fuel gas, pressurized gas formed adverse current to passage.
Described heat exchanger (2) one end connects diffuser pipe (3), cowling (4), gas inlet chamber (5) is formed between diffuser pipe (3) and cowling (4), this air-inlet cavity (5) is arranged on outside described heat exchanger (2) excircle, heat exchanger (2) inner circumference extends to form a gas outlet chamber (6), and combustion gas flows to gas outlet chamber (6) from heat exchanger (2) outer radial along gas inlet chamber (5).
The other end of described heat exchanger arranges pressurized gas suction tude (7), high pressure admission steam outlet pipe (8), pressurized gas suction tude (7) is evenly equipped with the pressurized air intake manifold (9) be communicated with described heat exchange core heat exchange import (8) of some annular settings along its circumferencial direction, pressurized gas steam outlet pipe (8) is evenly equipped with that some annulars are arranged and that described heat exchange core heat exchange outlet (9) is communicated with pressurized air along its circumferencial direction to give vent to anger manifold (10): described pressurized air manifold (10) of giving vent to anger is arranged on pressurized air intake manifold (9) inner side, pressurized air and high-temperature fuel gas are flowed to reverse.
Described fixed support arm (22) is arranged on pressurized gas side, and float support arm (23) is arranged on the side of high-temperature fuel gas; Fixed support arm (22) is exposed among air, and it is inner that float support arm (23) is arranged on cowling (4).
A heat transfer process for the gas turbine regenerator of solid of rotation layout, carries out according to following steps:
High-temperature fuel gas enters gas inlet chamber (5) from diffuser pipe (3), cowling (4), pressurized gas enter heat exchange core heat exchange import (8) from pressurized gas suction tude (7), pressurized air intake manifold (9), in heat transfer process, high-temperature fuel gas flows to the gas outlet chamber (6) of heat exchanger (2) inner circumference formation from the gap of heat exchanger (2) outside from the excircle of heat exchanger (2); Pressurized gas from the passage that heat exchanger (2) inside is formed to flow to from heat exchanger (2) the inner outer end formed and the adverse current of high-temperature fuel gas to, formation heat exchange;
Before carrying out heat exchange, by the diffuser pipe (3) of high-temperature fuel gas side, cowling (4) and gas inlet chamber (5), and the diameter of gas outlet chamber (6) is selected, by the flow control of high-temperature fuel gas at 25-35m/s;
To pressurized air air inlet with give vent to anger, its flow velocity is also controlled at 25-35m/s.
Advantage of the present invention is: for regenerator heat dissipating capacity problem, we have selected the plate fin type heat exchanger that compact structure, bearing capacity and rigidity are larger, and by solid of rotation layout, is integrated with more than ten regenerator core body, to increase heat dissipation potential; Adopt reflux type to arrange combustion gas and compressed-air actuated runner, make radiating efficiency reach the highest; And according to the difference of combustion gas side and pressurized air side temperature, pressure, density, adopt the fin structure of different heights to be optimized, improve the comprehensive heat dissipation potential of regenerator.
For gas turbine regenerator flow resistance problem, we are when runner design, by the diffuser pipe of combustion gas side, cowling and suction tude, and the arrangement of the diameter of gas outlet pipe, by the flow velocity of combustion gas, control at about 30m/s.To pressurized air air inlet with give vent to anger, according to the difference of different temperatures lower density, have employed uniform flow design equally.
For heat load and the thermal shock problem of gas turbine regenerator, on material selection, adopt resistance to heat good, coefficient of linear expansion is little, the heat-resistance stainless steel that thermal creep intensity is high.In minimizing heat load and thermal shock, by design, make each regenerator core body, all have relatively independent suspension, and an independent turnover compression air flow channel, what avoid between core body is implicative of each other, reduce the linear expansion of regenerator entirety, reduce heat load and impact; Each independent core body, all adopts submissiveization to design, and reduces the rigidity of core body component, avoids the stress under thermal expansion to concentrate.The suspension arrangement of core body, main fixed support design, outside the low temperature side of regenerator, contacts with ambient air, heat load and thermal distortion is reduced; Auxiliary float support, designs at cowling inner, by the protection of cowling, avoids the direct impact of heat load, cushioned.Owing to have employed solid of rotation design, heat exchanger entirety is the Flow and heat flux of axial symmetry, fluid, is also symmetrical balance, avoids the stress that thermal stress causes and concentrates.Meanwhile, take full advantage of the feature of heat exchanger combustion gas side pressure close to normal pressure, the wall thickness design of combustion gas runner is thinner, reduces the rigidity of runner, to adapt to the casing deformation that heat load causes, and does not affect sealing.
By taking above measure, the gas turbine regenerator of solid of rotation layout, follow occurring in nature, enclose during herbaceous plant opposing wind and rain and roll into a ball into a small bundle of straw, etc. for silkworms to spin cocoons on, every sheet leaf is all rooted in root system, separate submissive method, it is applied in regenerator, adopt the layout that revolution is symmetrical, each core body independent suspension, by reducing the rigidity of regenerator, it is made to adapt to thermal distortion because regenerator high temperature causes and thermal shock, improve the high temperature resistance thermal shock of regenerator and the ability of thermal distortion, meet the backheat operating mode needs of gas turbine, simultaneously, reduce manufacture cost, improve reliability.
Accompanying drawing explanation
Fig. 1 is structural representation of the present invention.
Fig. 2 is the positive direction view of Fig. 1.
Fig. 3 is the A-A direction view of Fig. 2.
Fig. 4 is heat converter structure schematic diagram of the present invention.
Fig. 5 is the front view of Fig. 4.
Fig. 6 is the side view of Fig. 4.
Fig. 7 is the plan view of Fig. 4.
1 be housing in figure, 2 be heat exchanger, 3 be diffuser pipe, 4 be cowling, 5 be gas inlet chamber, 6 be gas outlet chamber, 7 be pressurized gas suction tude, 8 be pressurized gas steam outlet pipe, 9 be pressurized air intake manifold, 10 for pressurized air manifold, 11 of giving vent to anger be that air inlet distribution cover, 12 to be confluxed for giving vent to anger cover;
21 be heat exchange core, 22 be fixed support arm, 23 for float support arm.
Embodiment
Regenerator of the present invention comprises housing 1, by the high-temperature fuel gas that Gas Turbine Power turbine is derived, jointly formed the gas inlet chamber 5 of high-temperature fuel gas by combustion gas diffusion 3, combustion gas cowling 4, flow into regenerator heat exchange core 21, carry out heat exchange with the pressurized air of about 550K.High-temperature fuel gas, is directed radially through heat exchange core 21 in regenerator inside, is aggregated into the center of heat exchanger 2, flows out regenerator by gas outlet chamber 6, leads to outside.Regenerator heat exchanger 2 is made up of one group of fan-shaped plate fin heat-exchanging core body 21, and adjoining one another by fan angle, together form the layout of solid of rotation.Direct connecting relation is not had between heat exchange core 21, separate, avoid the thermal stress each other that thermal expansion causes.Each regenerator heat exchange core 21, by regenerator fixed support arm 22 and regenerator float support arm 23, independent suspension is in regenerator blast tube.The pressurized air air inlet of gas turbine high-pressure compressor, by pressurized gas suction tude 7 and pressurized air air inlet distribution cover 11, be evenly distributed to pressurized air intake manifold 9, enter regenerator heat exchange core 21, edge and combustion gas countercurrent direction, flow out regenerator heat exchange core 21, to give vent to anger manifold 10 through pressurized air after heat exchange core 21 circulates, be aggregated into pressurized air to give vent to anger the cover 12 that confluxes, by pressurized air steam outlet pipe 8, flow into gas turbine gas generator.
Fixed support arm 22 of the present invention, float support arm 23 make heat exchange core 21 radial direction be retrained, make heat exchange core 21 can and pressurized air intake manifold 9, pressurized air manifold 10 of giving vent to anger accurately dock, avoid causing the problem of sealing because of heat exchange core 21 movement diametrically and avoiding the collision between manifold and heat exchange core 21 to cause both damages; The setting of float support arm 23 simultaneously makes heat exchange core 21 axial direction have certain floating, and cushions the impact because high-temperature fuel gas, pressurized gas bring, the working life of protection heat exchange 2.
The present invention is by the diffuser pipe of combustion gas side, cowling and suction tude, and the arrangement of the diameter of gas outlet pipe, by the flow velocity of combustion gas, controls at about 30m/s.To pressurized air air inlet with give vent to anger, according to the difference of different temperatures lower density, have employed uniform flow design equally.During design regenerator core body, by adjusting the width of fan angle and core body two ends, make up combustion gas when different temperatures, because density is different, the flow velocity caused is uneven, increases the fin height of combustion gas side runner, reduces flow velocity, minimizing flow resistance.By above-mentioned measure, by flow resistance, be reduced to the scope of allowing.
The give vent to anger radical of manifold 10 of pressurized air intake manifold 9 of the present invention, pressurized air is consistent with the number of heat exchange core 21, every root pressurized air intake manifold 9, pressurized air are given vent to anger a manifold 10 respectively corresponding heat exchange core 21, therefore pressurized gas when the flowing of each heat exchange core mutually independently, also gap is there is between heat exchange core 21 between adjacent, therefore the heat exchange area increased, improves heat transfer effect.
Claims (5)
1. a gas turbine regenerator for solid of rotation layout, is characterized in that, comprises housing (1), is provided with heat exchanger (2) in housing (1); Described heat exchanger (2) is made up of (21) the heat exchange core that a group is fan shape, each heat exchange core (21) hoop arranges formation one annular solid, each heat exchange core (21) is separate, establishes fixed support arm (22) and float support arm (23) in heat exchange core (21) both sides; Heat exchanger (2) formed high-temperature fuel gas, pressurized gas formed adverse current to passage.
2. the gas turbine regenerator of a kind of solid of rotation layout according to claim 1, it is characterized in that, described heat exchanger (2) one end connects diffuser pipe (3), cowling (4), gas inlet chamber (5) is formed between diffuser pipe (3) and cowling (4), this air-inlet cavity (5) is arranged on outside described heat exchanger (2) excircle, heat exchanger (2) inner circumference extends to form a gas outlet chamber (6), and combustion gas flows to gas outlet chamber (6) from heat exchanger (2) outer radial along gas inlet chamber (5).
3. the gas turbine regenerator of a kind of solid of rotation layout according to claim 1, it is characterized in that, the other end of described heat exchanger arranges pressurized gas suction tude (7), high pressure admission steam outlet pipe (8), pressurized gas suction tude (7) is evenly equipped with the pressurized air intake manifold (9) be communicated with described heat exchange core heat exchange import (8) of some annular settings along its circumferencial direction, pressurized gas steam outlet pipe (8) is evenly equipped with that some annulars are arranged and that described heat exchange core heat exchange outlet (9) is communicated with pressurized air along its circumferencial direction to give vent to anger manifold (10): described pressurized air manifold (10) of giving vent to anger is arranged on pressurized air intake manifold (9) inner side, pressurized air and high-temperature fuel gas are flowed to reverse.
4. the gas turbine regenerator of a kind of solid of rotation layout according to claim 2, is characterized in that, described fixed support arm (22) is arranged on pressurized gas side, and float support arm (23) is arranged on the side of high-temperature fuel gas; Fixed support arm (22) is exposed among air, and it is inner that float support arm (23) is arranged on cowling (4).
5. a heat transfer process for the gas turbine regenerator of solid of rotation layout, is characterized in that, carries out according to following steps:
High-temperature fuel gas enters gas inlet chamber (5) from diffuser pipe (3), cowling (4), pressurized gas enter heat exchange core heat exchange import (8) from pressurized gas suction tude (7), pressurized air intake manifold (9), in heat transfer process, high-temperature fuel gas flows to the gas outlet chamber (6) of heat exchanger (2) inner circumference formation from the gap of heat exchanger (2) outside from the excircle of heat exchanger (2); Pressurized gas from the passage that heat exchanger (2) inside is formed to flow to from heat exchanger (2) the inner outer end formed and the adverse current of high-temperature fuel gas to, formation heat exchange;
Before carrying out heat exchange, by the diffuser pipe (3) of high-temperature fuel gas side, cowling (4) and gas inlet chamber (5), and the diameter of gas outlet chamber (6) is selected, by the flow control of high-temperature fuel gas at 25-35m/s;
To pressurized air air inlet with give vent to anger, its flow velocity is also controlled at 25-35m/s.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410445138.2A CN104295374B (en) | 2014-09-03 | 2014-09-03 | A kind of the gas turbine regenerator and its heat transfer process of revolving body layout |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201410445138.2A CN104295374B (en) | 2014-09-03 | 2014-09-03 | A kind of the gas turbine regenerator and its heat transfer process of revolving body layout |
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| CN104295374A true CN104295374A (en) | 2015-01-21 |
| CN104295374B CN104295374B (en) | 2017-06-23 |
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| CN201410445138.2A Active CN104295374B (en) | 2014-09-03 | 2014-09-03 | A kind of the gas turbine regenerator and its heat transfer process of revolving body layout |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107044347A (en) * | 2017-05-23 | 2017-08-15 | 上海泛智能源装备有限公司 | A kind of regenerator and gas turbine |
Citations (5)
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| DE2443989A1 (en) * | 1973-10-24 | 1975-04-30 | Advanced Materials Eng | ROTARY PREHEAT EXCHANGER |
| WO2010135648A1 (en) * | 2009-05-22 | 2010-11-25 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Compact radial counterflow recuperator |
| CN103217028A (en) * | 2013-04-17 | 2013-07-24 | 高邮市荣清机械电子有限公司 | Fan-shaped radiator |
| CN203642748U (en) * | 2013-12-31 | 2014-06-11 | 河北科技大学 | Double-pipe heat exchanger for heat exchanging of various fluids |
| CN204126730U (en) * | 2014-09-03 | 2015-01-28 | 高邮市荣清机械电子有限公司 | A kind of gas turbine regenerator of solid of rotation layout |
-
2014
- 2014-09-03 CN CN201410445138.2A patent/CN104295374B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE2443989A1 (en) * | 1973-10-24 | 1975-04-30 | Advanced Materials Eng | ROTARY PREHEAT EXCHANGER |
| WO2010135648A1 (en) * | 2009-05-22 | 2010-11-25 | The Government Of The United States Of America, As Represented By The Secretary Of The Navy | Compact radial counterflow recuperator |
| CN103217028A (en) * | 2013-04-17 | 2013-07-24 | 高邮市荣清机械电子有限公司 | Fan-shaped radiator |
| CN203642748U (en) * | 2013-12-31 | 2014-06-11 | 河北科技大学 | Double-pipe heat exchanger for heat exchanging of various fluids |
| CN204126730U (en) * | 2014-09-03 | 2015-01-28 | 高邮市荣清机械电子有限公司 | A kind of gas turbine regenerator of solid of rotation layout |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107044347A (en) * | 2017-05-23 | 2017-08-15 | 上海泛智能源装备有限公司 | A kind of regenerator and gas turbine |
| CN107044347B (en) * | 2017-05-23 | 2019-09-17 | 新奥能源动力科技（上海）有限公司 | A kind of regenerator and gas turbine |
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| CN104295374B (en) | 2017-06-23 |
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