CN104110275B - A kind of advanced turbine cooling method circulated based on porous medium and supercritical state fluid - Google Patents
A kind of advanced turbine cooling method circulated based on porous medium and supercritical state fluid Download PDFInfo
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- CN104110275B CN104110275B CN201410314322.3A CN201410314322A CN104110275B CN 104110275 B CN104110275 B CN 104110275B CN 201410314322 A CN201410314322 A CN 201410314322A CN 104110275 B CN104110275 B CN 104110275B
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Abstract
A kind of advanced turbine blade cooling method circulated based on porous medium and supercritical state fluid, increase effective heat exchange area by dielectric material filling porous in the cooling channel in turbine blade, its effective heat exchange area depends on the shape of micropore structure, size and orientation; The supercritical state fluid that, exchange capability of heat little with flow resistance is strong is heat transferring medium, makes the actual heat exchange amount of turbine larger compared to conventional heat transfer mode; Can according to the cooling channel number in actual heat exchange Demand Design leaf dish and the floor number in blade; Can according to the how empty medium pore size of actual heat exchange Demand Design, shape and orientation; Blade is by rapid laser-shaping technique or other high energy beam rapid shaping technique overall processing; The direct rapid shaping of the present invention, technique is simple, and structure morpheme designability is strong.
Description
Technical field
The present invention relates to a kind of advanced turbine cooling method circulated based on porous medium and supercritical state fluid, be mainly used in reducing turbine blade heat load, improve turbine service life, belong to aeroengine and high-speed rotating machine technical field.
Background technique
Turbine inlet temperature decides the thermal efficiency of aeroengine.The raising of turbine inlet temperature can improve the efficiency of aeroengine, can reduce oil consumption rate and bring income economically, can improve unit area thrust obtain better mobility to military secret civil aircraft.And turbine inlet temperature can not unlimited increase, this is mainly subject to the restriction of turbine material, and temperature is too high can affect the intensity of material, toughness and working life.Current Fourth Generation Fighters is if the motor F119 turbine inlet temperature of F22 is close to 1800K, this forth generation single crystal alloy 1300K far above up-to-date development holds the warm limit, therefore must cool turbine blade, reduce its heat load, current Main Means to be bled cooling turbine bucket from gas compressor.
Be illustrated in figure 1 the typical turbine rotor blade type of cooling, it is high efficience motor (E3) the high-pressure turbine first order movable vane cooling system of the NASA of GE development of company, by the Air flow extracted out in the middle part of compressor diffuser.What can find out that this cooling system adopts by (a) in the cooling channel schematic diagram 1 of meridional section is that convection current and air film Cooling Design are strengthened in double loop.In anterior loop, leading edge impinging cooling is by the three flow process serpentine path air feed with fin flow-disturbing.Leading edge is also subject to gaseous film control, and gaseous film control is by three row radial skew hole air feed.Air required for pressure side gaseous film control is by the circular hole air feed of row's axioversion, and the gaseous film control air of suction surface is by the expanded bore air feed of row's axioversion.The serpentine path flowed by the forward direction of three flow belt flow-disturbing fins in second segment loop forms, simultaneously for the impinging cooling of the cylinder with ribbing of trailing edge provides air.The air of cooled blade trailing edge is flowed out by the air vent of pressure side, and forms outside gaseous film control at the remaining part of trailing edge.The shortcoming of this type of cooling is that heat exchange area is little, can only in such as Fig. 1 (b) 1. shown in cooling channel surrounding carry out heat exchange, effective heat exchange area is little; In addition, derive from the air in gas compressor due to cold air, this will certainly reduce the efficiency of motor.
Summary of the invention
The technology of the present invention is dealt with problems: overcome the deficiencies in the prior art, provides a kind of advanced turbine cooling method circulated based on porous medium and supercritical state fluid, has the advantage that heat transfer intensity is large, heat exchange efficiency is high.
Technical solution of the present invention: a kind of advanced turbine blade cooling method circulated based on porous medium and supercritical state fluid, its feature is: at this blade of the cooling channel of described blade filling porous medium wholly or in part, heat-exchange working medium in described porous medium is supercritical state fluid, the circulation of described supercritical state fluid is the circulation of enclosed intercooled regeneration, described supercritical state fluid circulation comprises the first miniature scale heat exchanger 11, second miniature scale heat exchanger 12, 3rd miniature scale heat exchanger 13, porous medium 14, suction booster 15, its relative position is right back is forward porous medium 14, 3rd miniature scale heat exchanger 13, second miniature scale heat exchanger 12, suction booster 15, first miniature scale heat exchanger 11, each parts connect successively by said sequence, and the first miniature scale heat exchanger 11 is connected with porous medium 14, form circulation.In the first miniature scale heat exchanger 11 of supercritical state fluid before high-pressure compressor, main flow is cooled in described supercritical state fluid circulation, in porous medium afterwards in high-pressure turbine 6 and low-pressure turbine 7,14 heat absorptions heat up, the 3rd miniature scale heat exchanger 13 after high-pressure compressor 4 carries out preheating to the gas entered before firing chamber 5, the the second miniature scale heat exchanger 12 flowing through by-pass air duct again cools, and the suction booster 15 pairs of supercritical state fluid pressurized utilizing high pressure stage to drive, form closed circulation before finally flowing back to high-pressure compressor 4; When by-pass air duct fluid cooling capacity is inadequate, flow out by with from fuel tank 9, the heat exchange in the second miniature scale heat exchanger 12 of the fuel after pump 10 supercharging is lowered the temperature.
The cooling channel structure of described blade is designed to single channel list rib structure, single channel trislab structure, Twin channel trislab structure or is any port number and floor number.
The material selection metallic aluminium foam, graphite foam, carbon foams, ceramic foam etc. of described porous medium.
Described supercritical state fluid comprises nitrogen, helium, water, carbon dioxide.
Described turbine blade is made up of the metallic material of thickness 1 ~ 20mm.
The shape of the hole of described porous medium, size and orientation are needed to control by actual heat exchange: make the product of effective heat exchange area and cold air working medium flow more greatly in heat load general goal by design hole, make actual heat exchange amount larger.
Air cooling passage is arranged between described porous medium and turbine blade surface.Blade still carries out gaseous film control and impinging cooling by the air in air cooling passage, and air can be cooled by the supercritical state fluid in porous medium, can improve the cooling effect to turbine blade.
Described cooling means can also be used on other blades needing the turbomachine of cooling or wheel disc.
The present invention's advantage is compared with prior art:
(1) advantage of the present invention compared with existing turbine cooling method: there is larger effective heat exchange area, heat transfer intensity is larger, heat exchange result make Turbine Blade Temperature Field evenly, thermal stress reduces; Avoid the problem causing engine efficiency to decline from bleed air, working medium used be nontoxic, nonstaining property, safety and environmental protection; Heat transfer process designability is strong, can carry out localized design, reach different heat transfer effects, can select not filling porous medium as required at the little place of thermal stress according to the thermal stress size of turbine blade to the pore character of porous medium; Utilize turbine of the present invention to apply to exceed the advanced pneumatic design of conventional design, improve turbine stage efficiency; Utilize turbine of the present invention lighter, and there is the performances such as damping shock absorption, acoustic energy absorption dissipation, electromagnetic shielding.
(2) the present invention utilizes porous media material to solve the problem of effective heat exchange area deficiency, as shown in Figure 3.By designing porous medium hole aperture shape, size and arrangement of apertures direction heat exchanging area.Cooling medium selects supercritical state fluid to solve the problem reducing engine efficiency from bleed air.
(3) the present invention relates to the feature that supercritical state fluid has low temperature, high specific heat capacity, low flow resistance, heat exchange amount can be ensured under small flow.The heterogeneous object that the fluid be full of in slight void between the skeleton that porous medium is made up of solid matter and skeleton forms, has lightweight, high specific strength, high specific stiffness and good also design.At the inner filling porous medium of turbine blade, take porous medium as the increase that heat-exchange carrier can realize heat exchange area, supercritical state fluid completes heat exchange with seepage flow motion mode and turbine blade in porous medium.
In a word, utilize a kind of porous medium and the circulation of supercritical state fluid, realize a kind of new turbine blade cooling.This cooling technology has the advantage that heat transfer intensity is large, heat exchange efficiency is high.Utilize this technology, turbine blade can realize the advantage of lightweight, high specific strength, high specific stiffness, long-life, and porous medium can also play the effect of damping shock absorption simultaneously.This technology has also reserved space for military-civil motor of future generation improves turbine inlet temperature further.
Accompanying drawing explanation
Fig. 1 is E3 engine high pressure turbine first order movable vane cooling system schematic diagram; Wherein a is the cooling channel schematic diagram of turbine blade meridional section, and b is the cooling channel schematic diagram of turbine blade 50% leaf height cross section;
Fig. 2 is that intercooled regeneration loop arrangement mode circulates schematic diagram;
Fig. 3 is turbine blade schematic cross-section of the present invention;
Fig. 4 is single channel list floor form cooling channel of the present invention, porous medium full packing schematic diagram;
Fig. 5 is single channel trislab form cooling channel of the present invention, porous medium full packing schematic diagram;
Fig. 6 is Twin channel trislab form cooling channel of the present invention, porous medium full packing schematic diagram;
Fig. 7 is that porous medium of the present invention is partially filled schematic diagram;
Fig. 8 arranges air cooling access diagram between porous medium of the present invention and turbine blade surface.
Embodiment
A kind of advanced turbine cooling method circulated based on porous medium and supercritical state fluid of the present invention, blade profile as shown in Figure 2, in this blade, heat-exchange carrier is porous medium, and effective heat exchange area depends on the shape of micropore structure, size and orientation; Heat transferring medium is supercritical state fluid, and its macroscopical flow direction in blade depends on blade inner cooling channel structure; Blade is made up of certain thickness material, and blade profile can continue to use the conventional design of prior art, because cooling effect of the present invention is more excellent relative to the cooling effect of other form, so blade profile likely applies the advanced pneumatic design exceeding conventional design.
Supercritical state fluid is a kind of material having gaseous state and liquidus behavior concurrently, and its coefficient of viscosity and diffusion coefficient are close to gaseous state, and flow losses are little; And heat-transfer coefficient and density etc. are close to liquid, thermal capacitance is large, and exchange capability of heat is strong.So carry out heat exchange with supercritical state fluid can obtain the heat transfer effect that flow losses are low, heat exchange amount is large.In addition the chemical composition stability of supercritical state fluid; Environment friendly and pollution-free; Security is good, and avirulent is without danger; Wide material sources easily obtain.
Threshold state fluid is including, but not limited to nitrogen, helium, water, carbon dioxide.Described supercritical state fluid circulation is an enclosed intercooled regeneration circulation, as shown in Figure 2.In intercooled regeneration loop arrangement, described supercritical state fluid circulation comprises the first miniature scale heat exchanger 11, second miniature scale heat exchanger 12, the 3rd miniature scale heat exchanger 13, porous medium 14, suction booster 15, its relative position is right back is forward porous medium 14, the 3rd miniature scale heat exchanger 13, second miniature scale heat exchanger 12, suction booster 15, first miniature scale heat exchanger 11, each parts connect successively by said sequence, and the first miniature scale heat exchanger 11 is connected with porous medium 14, form circulation.In the first miniature scale heat exchanger 11 of supercritical state fluid before high-pressure compressor, main flow is cooled in described supercritical state fluid circulation, in porous medium afterwards in high-pressure turbine 6 and low-pressure turbine 7,14 heat absorptions heat up, the 3rd miniature scale heat exchanger 13 after high-pressure compressor 4 carries out preheating to the gas entered before firing chamber 5, the the second miniature scale heat exchanger 12 flowing through by-pass air duct again cools, and the suction booster 15 pairs of supercritical state fluid pressurized utilizing high pressure stage to drive, form closed circulation before finally flowing back to high-pressure compressor 4; When by-pass air duct fluid cooling capacity is inadequate, flow out by with from fuel tank 9, the heat exchange in the second miniature scale heat exchanger 12 of the fuel after pump 10 supercharging is lowered the temperature.
Porous medium is the material that the skeleton be made up of solid matter and the intensive micro-pore be divided into by skeleton form, and has superior designability as a kind of engineering functional material, has excellent physical property and good mechanical property simultaneously.Described porous medium internal void is interconnected, and pore-size is much larger than fluid molecule mean free path, and choosing is less than the macro-size of porous medium, and aperture can be decreased to micron order and even nanometer by grade.Porous media material can be selected but be not limited to the light-weight metals such as aluminium.Described cooling channel structure is different from conventional chilling channel form, and reason is the circulation of supercritical state fluid is closed loop.
Embodiment 1:
A high-pressure turbine movable vane as shown in Figure 4, blade profile has met the performance requirement of engine total to turbine part through pneumatic design.Turbine blade internal cooling channel be designed to single channel (as in Fig. 4 1. shown in), arrange in blade a floor (as in Fig. 4 2. shown in), and claim the structural type of this cooling channel to be single channel list floor form.Porous medium is filled in the cooling channel in blade completely, and the hole of porous medium is designed to circle, average diameter 300 microns, and arrangement mode adopts class sandstone accumulation body.Supercritical state fluid enters porous medium from vane nose radial inflow cooling channel, moves to rear end in seepage flow mode, flows out blade, flow 80kg/s.By this type of cooling, turbine surfaces temperature can be reduced 200k again on the basis of conventional heat transfer mode.According to the power load distributing situation of blade reality, at load larger part, bore dia can be enlarged to 500 microns.
After the spatial distribution structure designing turbine blade and porous medium hole, carry out machining blade by rapid laser-shaping technique, or the cladding rapid shaping technique of any kind high energy beam of similar use.
Embodiment 2:
As a kind of advanced turbine blade cooling method circulated based on porous medium and supercritical state fluid in embodiment 1, the cooling channel wherein in turbine is single channel () the trislab () structural type shown in Fig. 5 in Fig. 5 1. in Fig. 5 2..
Embodiment 3:
As a kind of advanced turbine blade cooling method based on porous medium and the circulation of supercritical state fluid in embodiment 1, the cooling channel wherein in turbine is Twin channel (in Fig. 6 1. 2.) the trislab () structural type shown in Fig. 6 in Fig. 6 3..
Embodiment 4:
As a kind of advanced turbine blade cooling method circulated based on porous medium and supercritical state fluid in embodiment 1-3, the cooling channel wherein in turbine can need to design any port number and floor number according to actual heat exchange.
Embodiment 5:
As a kind of advanced turbine blade cooling method circulated based on porous medium and supercritical state fluid in embodiment 1-4, at the little place of turbine blade heat load, can not filling porous medium, as shown in Figure 7, the heat transfer requirements so not only ensured but also as far as possible reduce turbine blade weight.
Embodiment 6:
As a kind of advanced turbine blade cooling method circulated based on porous medium and supercritical state fluid in embodiment 1-5, air cooling passage () can be arranged between porous medium and turbine blade surface in Fig. 8 1., air forms the conventional turbine cooling mode such as impinging cooling and gaseous film control as direct heat transfer medium, supercritical state fluid is used for cooling-air as indirect heat exchange medium, makes the effect of impinging cooling and gaseous film control better relative to conventional chilling.
Embodiment 7:
As a kind of advanced turbine blade cooling method circulated based on porous medium and supercritical state fluid in embodiment 1-6, the hole of porous medium can be designed to ellipse, irregularly shaped and difform combination.Bore dia can heat exchange need to select between 1 ~ 1000 micron.
Embodiment 8:
As a kind of advanced turbine blade cooling method based on porous medium and the circulation of supercritical state fluid in embodiment 1-7, described turbine blade by other techniques as the various manufacturing process of EDM, soldering, electrochemistry and foam metal or any suitable manufacturing process are processed.
Embodiment 9:
As a kind of advanced Cooling Technique Based On Thermal Driving circulated based on porous medium and supercritical state fluid in embodiment 1-8, for the blade and the wheel disc that need heat exchange of various turbomachine.
In a word, heat-exchange carrier of the present invention is porous medium, and heat transfer effect quality depends on the pore shape of porous medium, size and orientation; Heat transferring medium is supercritical state fluid, and supercritical state fluid forms an enclosed intercooled regeneration circulation; Blade surface is made up of certain thickness metallic material, and porous medium is filled in blade and is fixed with one with blade, by laser or the processing of other high energy beam rapid shaping technique; It can be used in modern military, the turbine rotor blade of civilian motor or stator blade,
Obviously, for the person of ordinary skill of the art, other mode of execution also may be made with reference to embodiment mentioned above.All embodiments are above exemplary instead of circumscribed.All amendments within the essence of claim technological scheme of the present invention all belong to its scope required for protection.
Claims (8)
1., based on the turbine blade cooling method that porous medium and supercritical state fluid circulate, it is characterized in that: at this blade of the cooling channel of described blade filling porous medium wholly or in part, heat-exchange working medium in described porous medium is supercritical state fluid, the circulation of described supercritical state fluid is the circulation of enclosed intercooled regeneration, and described supercritical state fluid circulation is made up of the first miniature scale heat exchanger (11), the second miniature scale heat exchanger (12), the 3rd miniature scale heat exchanger (13), porous medium (14), suction booster (15), porous medium (14), the 3rd miniature scale heat exchanger (13), the second miniature scale heat exchanger (12), suction booster (15), the first miniature scale heat exchanger (11), each parts connect successively by said sequence, and the first miniature scale heat exchanger (11) is connected with porous medium (14), form circulation, in the first miniature scale heat exchanger (11) of supercritical state fluid before high-pressure compressor, main flow is cooled in described supercritical state fluid circulation, in porous medium (14) afterwards in high-pressure turbine (6) and low-pressure turbine (7), heat absorption heats up, the 3rd miniature scale heat exchanger (13) after high-pressure compressor (4) carries out preheating to the gas entering firing chamber (5) front, the the second miniature scale heat exchanger (12) flowing through by-pass air duct again cools, and the suction booster utilizing high pressure stage to drive (15) is to supercritical state fluid pressurized, finally flow back to the front formation closed circulation of high-pressure compressor (4), when by-pass air duct fluid cooling capacity is inadequate, flow out by means of from fuel tank (9), the heat exchange in the second miniature scale heat exchanger (12) of the fuel after pump (10) supercharging is lowered the temperature.
2. the turbine blade cooling method circulated based on porous medium and supercritical state fluid according to claim 1, is characterized in that: the cooling channel structure of described blade is designed to single channel list rib structure, single channel trislab structure, Twin channel trislab structure.
3. the turbine blade cooling method based on porous medium and the circulation of supercritical state fluid according to claim 1, is characterized in that: the material selection metallic aluminium foam of described porous medium, graphite foam, carbon foams or ceramic foam.
4. the turbine blade cooling method circulated based on porous medium and supercritical state fluid according to claim 1, is characterized in that: described supercritical state fluid is nitrogen, helium, water, carbon dioxide.
5. the turbine blade cooling method circulated based on porous medium and supercritical state fluid according to claim 1, is characterized in that: described turbine blade is made up of the metallic material of thickness 1 ~ 20mm.
6. the turbine blade cooling method circulated based on porous medium and supercritical state fluid according to claim 1, it is characterized in that: the shape of the hole of described porous medium, size and orientation are needed to control by actual heat exchange: make the product of effective heat exchange area and cold air working medium flow more greatly in heat load general goal by design hole, make actual heat exchange amount larger.
7. the turbine blade cooling method circulated based on porous medium and supercritical state fluid according to claim 1, is characterized in that: between described porous medium and turbine blade surface, arrange air cooling passage.
8. the turbine blade cooling method based on porous medium and the circulation of supercritical state fluid according to claim 1, is characterized in that: described cooling means can also be used on the blade of turbomachine or wheel disc that other needs cool.
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| US3067982A (en) * | 1958-08-25 | 1962-12-11 | California Inst Res Found | Porous wall turbine blades and method of manufacture |
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| US3656863A (en) * | 1970-07-27 | 1972-04-18 | Curtiss Wright Corp | Transpiration cooled turbine rotor blade |
| GB2042648A (en) * | 1979-02-24 | 1980-09-24 | Rolls Royce | Gas turbine engine hollow blades |
| CN102536333A (en) * | 2011-01-03 | 2012-07-04 | 通用电气公司 | Turbomachine airfoil component and cooling method therefor |
| CN103221640A (en) * | 2010-09-21 | 2013-07-24 | 帕尔默实验室有限责任公司 | High efficiency power production methods, assemblies, and systems |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| JPH0915639A (en) * | 1995-06-28 | 1997-01-17 | Hitachi Ltd | Liquid crystal display device |
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Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB778672A (en) * | 1954-10-18 | 1957-07-10 | Parsons & Marine Eng Turbine | Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades |
| US3067982A (en) * | 1958-08-25 | 1962-12-11 | California Inst Res Found | Porous wall turbine blades and method of manufacture |
| US3365171A (en) * | 1965-06-16 | 1968-01-23 | Gen Electric | Fluid flow machine |
| US3656863A (en) * | 1970-07-27 | 1972-04-18 | Curtiss Wright Corp | Transpiration cooled turbine rotor blade |
| GB2042648A (en) * | 1979-02-24 | 1980-09-24 | Rolls Royce | Gas turbine engine hollow blades |
| CN103221640A (en) * | 2010-09-21 | 2013-07-24 | 帕尔默实验室有限责任公司 | High efficiency power production methods, assemblies, and systems |
| CN102536333A (en) * | 2011-01-03 | 2012-07-04 | 通用电气公司 | Turbomachine airfoil component and cooling method therefor |
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