CN104110275A - Advanced turbine cooling method based on porous media and super-critical state fluid circulation - Google Patents
Advanced turbine cooling method based on porous media and super-critical state fluid circulation Download PDFInfo
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- CN104110275A CN104110275A CN201410314322.3A CN201410314322A CN104110275A CN 104110275 A CN104110275 A CN 104110275A CN 201410314322 A CN201410314322 A CN 201410314322A CN 104110275 A CN104110275 A CN 104110275A
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Abstract
The invention discloses an advanced turbine cooling method based on porous media and super-critical state fluid circulation. According to the method, cooling channels in turbine blades are filled with porous media materials to increase the effective heat exchange area, and the effective heat exchange area depends on the shape, size and arraying direction of micro-pore structures; super-critical state fluid which is small in flowing resistance and high in heat exchange capacity serves as heat exchange media, so that the actual heat exchange amount is larger than the heat exchange amount in a conventional heat exchange model according to actual heat exchange requirements, and the number of cooling channels in the blades and the number of rib plates in the blades can be designed; according to the actual heat exchange requirements, the size, shape and arraying direction of the porous media can be designed; the blades can be machined integrally through a laser rapid forming technology or other high-energy-beam rapid forming technologies. The advanced turbine cooling method achieves direct and rapid forming, the technology is simple, and the structure, shape and position designability is high.
Description
Technical field
The present invention relates to a kind of advanced turbine cooling method based on porous medium and supercritical state Fluid Circulation, be mainly used in reducing turbine blade heat load, improve turbine operating life, belong to aeroengine and high-speed rotating machine technical field.
Background technique
Turbine inlet temperature is determining the thermal efficiency of aeroengine.The raising of turbine inlet temperature can improve the efficiency of aeroengine, can reduce oil consumption rate bring income economically to civil aircraft, can improve unit area thrust obtain better mobility to military secret.And the impossible unlimited increase of turbine inlet temperature, this is mainly subject to the restriction of turbine material, and excess Temperature can affect intensity, toughness and the working life of material.Current fourth generation fighter has approached 1800K as the motor F119 turbine inlet temperature of F22, this the 4th generation single crystal alloy 1300K far above up-to-date development holds the warm limit, therefore must carry out cooling to turbine blade, reduce its heat load, current Main Means is from the gas compressor cooling turbine bucket of bleeding.
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, and the air of being extracted out by gas compressor Diffuser middle part is cooling.What can find out by (a) in the cooling channel schematic diagram 1 in meridian cross section that this cooling system adopts is double loop strengthening convection current and air film Cooling Design.In anterior loop, leading edge is impacted cooling by the passage air feed that crawls with three flow processs of fin flow-disturbing.It is cooling that leading edge is also subject to air film, the cooling three row's radial skew hole air feed that pass through of air film.The cooling needed air of pressure side air film is by the circular hole air feed of row's axioversion, and the air film cooling-air of suction surface is by the expanded bore air feed of row's axioversion.The passage that crawls being flowed by the forward direction of three flow belt flow-disturbing fins in second segment loop forms, and is the cooling air that provides of impact of the cylinder with ribbing of trailing edge simultaneously.The air of cooled blade trailing edge flows out by the air vent of pressure side, and it is cooling to form outside air film at the remaining part of trailing edge.The shortcoming of this type of cooling is that heat exchange area is little, can only be carrying out heat exchange as (b) in Fig. 1 cooling channel surrounding as shown in 1., and effective heat exchange area is little; In addition,, because cold air derives from the air in gas compressor, 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, a kind of advanced turbine cooling method based on porous medium and supercritical state Fluid Circulation is provided, have advantages of 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 based on porous medium and supercritical state Fluid Circulation, 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, the 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, 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 described supercritical state Fluid Circulation, in the first miniature scale heat exchanger 11 of supercritical state fluid before high-pressure compressor, carry out cooling to main flow, in porous medium in high-pressure turbine 6 and low-pressure turbine 7,14 heat absorptions heat up afterwards, the 3rd miniature scale heat exchanger 13 after high-pressure compressor 4 carries out preheating to the gas entering before firing chamber 5, the the second miniature scale heat exchanger 12 of by-pass air duct of flowing through again cools, and utilize the suction booster 15 of high pressure stage drive to supercritical state fluid pressurized, finally flow back to the front formation closed circulation of high-pressure compressor 4; In the time that by-pass air duct fluid cooling capacity is inadequate, by with from fuel tank 9 flow out, the heat exchange in the second miniature scale heat exchanger 12 of the fuel after pump 10 superchargings 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 of described porous medium, graphite foam, charcoal foam, ceramic foam etc.
Described supercritical state fluid comprises nitrogen, helium, water, carbon dioxide.
Described turbine blade is made up of the metallic material of thickness 1～20mm.
Shape, size and the orientation of the hole of described porous medium needed to control by actual heat exchange: make the product of effective heat exchange area and cold air working medium flow larger in heat load general goal by design hole, make actual heat exchange amount larger.
Between described porous medium and turbine blade surface, arrange air cooling passage.It is cooling and impact coolingly that blade still carries out air film by the air in air cooling passage, and air can be cooling 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 or wheel disc that need cooling turbomachine.
The present invention's advantage is compared with prior art:
(1) advantage of the present invention compared with existing turbine cooling method: have larger effective heat exchange area, heat transfer intensity is larger, and heat exchange result makes Turbine Blade Temperature Field more even, and thermal stress reduces; Avoided the problem that causes engine efficiency to decline from gas compressor bleed, working medium used is nontoxic, nonstaining property, safety and environmental protection; Heat transfer process designability is strong, can carry out localized design to the pore character of porous medium according to the thermal stress size of turbine blade, reaches different heat transfer effects, can select as required not filling porous medium at the little place of thermal stress; 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 porous medium hole aperture shape, size and arrangement of apertures direction heat exchanging area are designed.Cooling medium selects supercritical state fluid to solve the problem that reduces engine efficiency from gas compressor bleed.
(3) the present invention relates to supercritical state fluid and have the feature of low temperature, high specific heat capacity, low flow resistance, can under small flow, ensure heat exchange amount.The heterogeneous object that the fluid being 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, can realize the increase of heat exchange area taking porous medium as heat-exchange carrier, 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 supercritical state Fluid Circulation, realize a kind of new turbine blade cooling.This cooling technology has advantages of that heat transfer intensity is large, heat exchange efficiency is high.Utilize this technology, turbine blade can be realized 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 been reserved space for military-civil motor of future generation further improves turbine inlet temperature.
Brief description of the drawings
Fig. 1 is E3 engine high pressure turbine first order movable vane cooling system schematic diagram; Wherein a is the cooling channel schematic diagram in turbine blade meridian cross section, and b is the cooling channel schematic diagram of the high cross section of turbine blade 50% leaf;
Fig. 2 is the intercooled regeneration loop arrangement mode schematic diagram that circulates;
Fig. 3 is turbine blade schematic cross-section of the present invention;
Fig. 4 is single channel list floor form of the present invention cooling channel, porous medium full packing schematic diagram;
Fig. 5 is single channel trislab form of the present invention cooling channel, porous medium full packing schematic diagram;
Fig. 6 is Twin channel trislab form of the present invention cooling channel, 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 based on porous medium and supercritical state Fluid Circulation 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 shape, size and the orientation of micropore structure; 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 be continued to use the conventional design of prior art, because the cooling effect of relative other form of cooling effect of the present invention is more excellent, so blade profile is likely applied the advanced pneumatic design that exceeds conventional design.
Supercritical state fluid is a kind of material that has gaseous state and liquid character concurrently, and its coefficient of viscosity and diffusion coefficient approach gaseous state, and flow losses are little; And heat-transfer coefficient and density etc. approach liquid state, thermal capacitance is large, and exchange capability of heat is strong.Can obtain so carry out heat exchange with supercritical state fluid 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, the 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, 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 described supercritical state Fluid Circulation, in the first miniature scale heat exchanger 11 of supercritical state fluid before high-pressure compressor, carry out cooling to main flow, in porous medium in high-pressure turbine 6 and low-pressure turbine 7,14 heat absorptions heat up afterwards, the 3rd miniature scale heat exchanger 13 after high-pressure compressor 4 carries out preheating to the gas entering before firing chamber 5, the the second miniature scale heat exchanger 12 of by-pass air duct of flowing through again cools, and utilize the suction booster 15 of high pressure stage drive to supercritical state fluid pressurized, finally flow back to the front formation closed circulation of high-pressure compressor 4; In the time that by-pass air duct fluid cooling capacity is inadequate, by with from fuel tank 9 flow out, the heat exchange in the second miniature scale heat exchanger 12 of the fuel after pump 10 superchargings is lowered the temperature.
Porous medium is the material that the skeleton being made up of solid matter and the intensive micro-pore being 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 cooling channel form, and reason is that supercritical state Fluid Circulation is for closing circulation.
Embodiment 1:
A high-pressure turbine movable vane as shown in Figure 4, blade profile has met the totally performance requirement to turbine part of motor through pneumatic design.Turbine blade internal cooling channel be designed to single channel (as in Fig. 4 1. as shown in), arrange in blade a floor (as in Fig. 4 2. as shown in), and claim that the structural type of this cooling channel is 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, 300 microns of average diameters, and arrangement mode adopts class sandstone accumulation body.Supercritical state fluid enters porous medium from blade front end 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 on the basis of conventional heat exchange mode again to 200k.Can, according to the load distribution situation of blade reality, at load larger part, bore dia be enlarged to 500 microns.
Designing after the space distribution structure of turbine blade and porous medium hole, can carry out machining blade by rapid laser-shaping technique, or similarly use the cladding rapid shaping technique of any kind high energy beam.
Embodiment 2:
As a kind of advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation in embodiment 1, wherein the cooling channel in turbine is the single channel shown in Fig. 5 (in Fig. 5 1.) trislab (in Fig. 5 2.) structural type.
Embodiment 3:
As a kind of advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation in embodiment 1, wherein the cooling channel in turbine is the Twin channel shown in Fig. 6 (in Fig. 6 1. 2.) trislab (in Fig. 6 3.) structural type.
Embodiment 4:
As a kind of advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation in embodiment 1-3, wherein any port number and floor number can need to be designed according to actual heat exchange in the cooling channel in turbine.
Embodiment 5:
As a kind of advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation 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 exchange so not only having ensured requires but also has reduced turbine blade weight as far as possible.
Embodiment 6:
As a kind of advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation in embodiment 1-5, can between porous medium and turbine blade surface, arrange air cooling passage (in Fig. 8 1.), air forms as direct heat transfer medium the cooling and conventional turbine cooling mode of the cooling grade of air film of impacting, supercritical state fluid is used for cooling-air as indirect heat exchange medium, makes to impact effect cooling and that air film is cooling cooling better with respect to routine.
Embodiment 7:
As a kind of advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation in embodiment 1-6, the hole of porous medium can be designed to ellipse, irregularly shaped and difform combination.Bore dia can need to be selected between 1～1000 micron in heat exchange.
Embodiment 8:
As a kind of advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation in embodiment 1-7, described turbine blade can be processed as the various manufacturing process of EDM, soldering, electrochemistry and foam metal or any suitable manufacturing process by other techniques.
Embodiment 9:
As a kind of advanced Cooling Technique Based On Thermal Driving based on porous medium and supercritical state Fluid Circulation in embodiment 1-8, for the blade that needs heat exchange and the wheel disc of various turbomachines.
In a word, heat-exchange carrier of the present invention is porous medium, and heat transfer effect quality depends on pore shape, size and the orientation of porous medium; 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 the turbine rotor blade or stator blade of modern military, civilian motor,
Obviously, for the person of ordinary skill of the art, also may make other mode of execution 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. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation, 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, described supercritical state Fluid Circulation comprises 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), its relative position is right back is forward 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 described supercritical state Fluid Circulation, in the first miniature scale heat exchanger (11) of supercritical state fluid before high-pressure compressor, carry out cooling to main flow, in porous medium in high-pressure turbine (6) and low-pressure turbine (7), (14) heat absorption heats up afterwards, the 3rd miniature scale heat exchanger (13) after high-pressure compressor (4) carries out preheating to entering the front gas in firing chamber (5), the the second miniature scale heat exchanger (12) of by-pass air duct of flowing through again cools, and utilize the suction booster (15) of high pressure stage drive to supercritical state fluid pressurized, finally flow back to the front formation closed circulation of high-pressure compressor (4), in the time that by-pass air duct fluid cooling capacity is inadequate, by with from fuel tank (9) flow out, the heat exchange in the second miniature scale heat exchanger (12) of the fuel after pump (10) supercharging is lowered the temperature.
2. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation 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 or is any port number and floor number.
3. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation according to claim 1, is characterized in that: material selection metallic aluminium foam, graphite foam, charcoal foam or the ceramic foam of described porous medium.
4. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation according to claim 1, is characterized in that: described supercritical state fluid comprises nitrogen, helium, water, carbon dioxide.
5. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation according to claim 1, is characterized in that: described turbine blade is made up of the metallic material of thickness 1～20mm.
6. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation according to claim 1, it is characterized in that: shape, size and the orientation of the hole of described porous medium needed to control by actual heat exchange: make the product of effective heat exchange area and cold air working medium flow larger in heat load general goal by design hole, make actual heat exchange amount larger.
7. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation according to claim 1, is characterized in that: between described porous medium and turbine blade surface, arrange air cooling passage.
8. the advanced turbine blade cooling method based on porous medium and supercritical state Fluid Circulation according to claim 1, is characterized in that: described cooling means can also be used on the blade or wheel disc of the cooling turbomachine of other needs.
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Cited By (1)
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| CN105386793A (en) * | 2014-11-12 | 2016-03-09 | 熵零股份有限公司 | Non-gas fluid backlash thermal dynamic conversion method and engine adopting method |
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