CN106089316A - A kind of stator part projective table type periodic pressure wave generation device - Google Patents
A kind of stator part projective table type periodic pressure wave generation device Download PDFInfo
- Publication number
- CN106089316A CN106089316A CN201610383125.6A CN201610383125A CN106089316A CN 106089316 A CN106089316 A CN 106089316A CN 201610383125 A CN201610383125 A CN 201610383125A CN 106089316 A CN106089316 A CN 106089316A
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- Prior art keywords
- stator
- air
- flow
- cooling
- rotor
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
Abstract
The invention discloses a kind of stator part projective table type periodic pressure wave generation device, be made up of stator, rotor scroll dish, turbine shaft, stator and rotor scroll dish are arranged in turbine shaft, form cooling flow channel between stator and the coaxial rotor turbine disk.Corresponding with the hole site of being bullied on rotor scroll dish by the boss structure on stator wall so that the stream pressure entering rotor scroll dish presents the feature of pressure oscillation in time, and presents periodic regularity change.Effect by periodic pressure ripple so that from the pressure oscillation air-flow entered by pore after entering turbo blade from blade bottom, at blade inner cooling channel, there is higher rate of heat transfer；Pressure wave air-flow, after air film hole ejection blade surface, can increase substantially the cooling effect of turbo blade, improve blade working reliability and life-span；Under the conditions of same life, significantly save the usage amount of cooling air-flow, effectively promote complete machine operating characteristic.
Description
Technical field
The present invention relates to Cooling Technique Based On Thermal Driving, specifically, relate to a kind of stator part projective table type periodic pressure ripple
Generator.
Technical background
Turbine is one of vitals of gas turbine or aero-engine, and before improving turbine, inlet temperature is to increase combustion gas
Turbine or aero-engine output and the effective measures of work efficiency.Turbine inlet temperature (TIT) has reached a 2000K left side at present
The right side, considerably beyond the resistance to extreme temperature manufacturing turbo blade material, it is therefore necessary to turbo blade is taked cooling technology, to ensure whirlpool
The reliability and stability of wheel work, its major measure is to bleed from compressor to cool down turbo blade.Advanced cooling
Technology, can cool down mesh ground by using less cooling gas to reach, thus have more gas participate in burning and do work turbine.
The cooling technology of turbo blade at present, mainly under steady pressure or flow Supplying gas condition, the inside to blade
Structure and outside film hole structure and layout improve, and to improve cooling effectiveness, and achieve good effect, but reach not yet
Limit of utilization to gas.Existing research finds, uses surge pressure supply, can further improve blade interior channel for heat exchange
Speed and outside gas film cooling efficiency, thus blade is cooled down by more good utilisation gas, improves cooling effectiveness.
Document Influence of Near Hole Pressure Fluctuation on the Thermal
Protection of a Film-Cooled Flat Plate(J.Heat Transfer.2009；131(2):022202-
Research 022202-11.) shows, in the case of vibration frequency is relatively big, carries the air film hole jet pair of periodic pressure fluctuation
Wall air film has extraordinary protective effect, has and imitates than the air film hole more preferable discharging characteristic of voltage stabilizing jet and gaseous film control
Rate；At document Heat transfer enhancement in the oscillating turbulent flow of a
Pluse combustor tail pipe [J] (Int.J.Heat, 1992,35:2311-2325) have studied fluctuation burner
Exit flow heat transfer characteristic, finds that the fluctuation air-flow of vibration frequency f about 80Hz can increase substantially the heat exchange efficiency of system；Literary composition
The research offering " in laminar flow, pulse pneumatic is horizontal plunders flat board augmentation of heat transfer " [J] (Journal of Chemical Industry and Engineering, 2012,06:1717-1722) shows,
Carry pressure oscillation ground air-flow, the heat exchange property of the heat flux planes such as air-flow enhances effectively that fluctuate, also enhance gas simultaneously
Heat transfer within Liu.
Although existing domestic and international research shows that the air-flow that periodic pressure fluctuates is entering blade from blade bottom tongue-and-groove
Behind inside, having higher rate of heat transfer in blade interior cooling duct, pressure wave air-flow is spraying blade surface from air film hole
After there is higher Film Cooling.But the pressure oscillation supply of major part research derives from the fluctuation gas that compressor produces
Stream, on the one hand compressor fluctuation air-flow is after walking around combustor entrance turbo blade inside, and pressure oscillation loss is bigger；Another
Aspect, this pressure oscillation characteristic is the most uncontrollable, can not be applied to gas turbine and obtain optimal heat exchange, cooling effect.
Summary of the invention
The deficiency existed in order to avoid prior art, the present invention proposes a kind of stator part projective table type periodic pressure ripple and produces
Device.
The technical solution adopted for the present invention to solve the technical problems is: include stator, rotor scroll dish, turbine shaft,
Stator and rotor scroll dish are arranged in turbine shaft；Described stator is spill disc structure, according to stator central shaft hole circumference all
Be furnished with some identical air inlets, on stator internal face circumference uniform some identical boss, and each boss, air inlet with in
Arbor hole is radially disposed on same straight line, and boss is identical with air inlet quantity；The uniform some phases of circumference on described rotor scroll dish
With tongue-and-groove, have radial cooling hole between tongue-and-groove, on rotor scroll Pan Bi, circumference is evenly equipped with some identical by pore, Mei Geshou
It is connected by Cooling Holes between pore with corresponding tongue-and-groove, turbine rotor blade is installed between tongue-and-groove；Boss on stator internal face
Relative with the hole site of being bullied on rotor scroll dish, form cooling flow channel between stator and rotor scroll dish.
Air inlet pass on described stator is circular or oval.
Boss on described stator wall is semicircular arc or half elliptic.
It is all circle or ellipse by pore and Cooling Holes pass structure on described rotor scroll dish；By pore, cold
But the turbine rotor blade quantity between hole with tongue-and-groove is equal.
Between stator and rotor scroll dish, axial gap is less than 2mm.
It is in turbine disk chamber, the boss on stator internal face is relative with the hole site of being bullied on rotor scroll dish so that
The pressure of the air-flow entering rotating disk presents the feature of pressure oscillation in time, and presents periodic Changing Pattern.Wherein, use
Cooling air-flow in turbine interior cooling flows out from pre-screw outlet, and a part of air-flow A enters turbine interior, air-flow A from air inlet
Pressure be metastable.After air-flow A enters in the turbine disk, due to centrifugal force and the effect of pressure reduction, air-flow A starts to far
Spread from the direction of turbine wheel shaft, be converted into the flow regime of air-flow D.For each is by pore, due to rotor scroll dish
Rotary action, relatively have circumference interval boss constantly extrude the air-flow D near by pore, circumference equally distributed
Under the effect of boss, the stable air-flow D of final pressure is converted into the air-flow B with periodic pressure fluctuation.A part of air-flow B turns
Turn to air-flow C enter in Cooling Holes, be used as the cooling air-flow of turbine blade cooling system, and carry periodic pressure ripple
Dynamic；Another part air-flow B can flow into turbine interior, for the cooling air-flow of other position of turbine.Pressure oscillation air-flow is from leaf
After entering blade interior bottom sheet, having higher rate of heat transfer in blade interior cooling duct, pressure wave air-flow is from air film
After hole ejection blade surface, there is higher Film Cooling.
Beneficial effect
The stator part projective table type periodic pressure wave generation device that the present invention proposes.By the boss on stator wall with turn
Periodically being acted on by pore on the sub-turbine disk, by the stream reforming air-flow for periodic pressure fluctuation of pressure stability, increases
With the heat exchange rate of blade inwall and the gas film cooling efficiency after blade air film hole sprays after air blast entrance turbo blade, carry
The high cooling effect to turbo blade.
The present invention relative to the air-flow of the pressure stability in existing cooling technology, pressure oscillation produced by this device
Air-flow, can produce more preferable blade cooling effect, improves blade working reliability and life-span；Or under the conditions of same life, greatly
The usage amount of amplitude saving cooling air-flow.
The present invention has the air-flow of periodic pressure wave effect can reduce the flow losses of running system, for turbine cooling
System complex working environment has more preferable adaptability；
The characteristic of pressure wave of the present invention can be carried out according to the existing cooling duct of blade interior or film hole structure type
Adjust, it is thus achieved that optimal pressure oscillation characteristic；Or according to the feature of pressure wave, the blade interior knot that design adapts therewith
Structure and film hole structure, play flowing and the heat exchange aspect maximum cooling potential of pressure wave air-flow.
The present invention utilizes the air-flow with controlled surge pressure feature produced required for cooling blade, effectively promotes
Complete machine operating characteristic.
Accompanying drawing explanation
With embodiment, one stator part projective table type periodic pressure wave generation device of the present invention is made below in conjunction with the accompanying drawings
Further describe.
Fig. 1 is that stator part projective table type periodic pressure wave generation device partly cuts open schematic diagram.
Fig. 2 is the stator part projective table type axial sectional view of periodic pressure wave generation device.
Fig. 3 is stator part projective table type periodic pressure wave generation device air flow outlet arrangement partial enlarged drawing.
Fig. 4 is the stator axonometric chart of stator part projective table type periodic pressure wave generation device.
Fig. 5 a, Fig. 5 b are the rotor scroll dish schematic diagram of stator part projective table type periodic pressure wave generation device.
In figure
1. stator 2. rotor scroll dish 3. turbine shaft 4. air inlet 5. tongue-and-groove 6. Cooling Holes 7. is convex by pore 8.
Platform
A. the air-flow B. flowing into turbine disk pressure stability has the air-flow of periodic pressure fluctuation
C. for the air-flow D. turbine disk intracavity air-flow of the outside cooling system of the turbine disk
Detailed description of the invention
The present embodiment is a kind of stator part projective table type periodic pressure wave generation device.
Refering to Fig. 1～Fig. 5 a, Fig. 5 b, the present embodiment stator part projective table type periodic pressure wave generation device, by stator 1,
Rotor scroll dish 2, turbine shaft 3 form, and stator 1 and rotor scroll dish 2 are arranged in turbine shaft 3.Wherein, stator 1 is recessed
Shape disc structure, has some identical cooling air-flow air inlets 4 according to stator 1 central shaft hole is circumferentially distributed, and the pass of air inlet 4 is
Circular or oval.On the concave surface of stator 1, circumference is machined with some identical boss 8, and boss is semicircular arc or half ellipse
Circle, and each boss 8, air inlet 4 be centrally located on same straight line with stator 1 axis hole, boss 8 is identical with air inlet 4 quantity.
On rotor scroll dish 2, the uniform some identical tongue-and-grooves 5 of circumference, have radial cooling hole 6, on rotor scroll Pan Bi between tongue-and-groove 5
Circumference is evenly equipped with some identical by pore 7, each is connected by Cooling Holes 6 by between pore 7 with corresponding tongue-and-groove 5, tongue-and-groove
Between install turbine rotor blade.It is all circle or ellipse by pore 7 and Cooling Holes 6 pass structure on rotor scroll dish 2
Shape；Equal with the turbine rotor blade quantity between tongue-and-groove 5 by pore 7, Cooling Holes 6.
In the course of the work, the cooling air-flow for turbine interior cooling flows out from pre-screw outlet, and wherein, air-flow A is from entering
Pore 4 enters turbine interior, and the pressure of air-flow A is metastable, after air-flow A enters turbine disk intracavity, due to centrifugal force
With the effect of pressure reduction, air-flow A starts to spread to the direction away from turbine wheel shaft 3, is converted into the flow regime of air-flow D.Boss 8 is the most right
Will enter and be carried out disturbance compression by the cooling air-flow of pore 7, under the effect of circumferential equally distributed boss 8, final pressure
Stable air-flow D is converted into has air-flow B, the air-flow B entrance of periodic pressure fluctuation by pore 7, and a part of air-flow B converts
Enter in Cooling Holes 6 for air-flow C, be used as the cooling air-flow of turbine blade cooling system, and carry periodic pressure fluctuation；
Another part air-flow B then flows into turbine interior, for the cooling air-flow of other position of turbine.Pressure oscillation air-flow is from the bottom of blade
After portion enters blade interior, having higher rate of heat transfer in blade interior cooling duct, pressure wave air-flow is spraying from air film hole
There is after going out blade surface preferable Film Cooling.
Embodiment 1
In the present embodiment, a diameter of 570mm of stator, the axial width of stator is 40mm, top, air current flow space upper wall
Face and axle center distance R3For 270mm.Wherein, air inlet heart distance axle center R5For 130mm, a diameter of 20mm of air inlet, select 16
Air inlet is uniformly distributed circumferentially, and air inlet hole depth is 15mm.Boss is half elliptic, boss centre distance axle center R1For
225mm, angle theta between two boss1Being 22.5 °, boss quantity is 16 and is uniformly distributed circumferentially.Rotor scroll dish a diameter of
570mm, axial width is 40mm, top, air current flow space upper wall surface and axle center distance R4For 270mm, turbine shaft is a diameter of
50mm.Wherein, by pore hole heart distance axle center R2For 225mm, two of which is by angle theta between pore2It it is 11.25 °, by pore hole
Footpath is 10mm, a length of 40mm in hole, and hole number of being bullied is 32 and is uniformly distributed circumferentially.Cooling Holes connects by pore and tongue-and-groove, cold
But aperture, hole is 10mm, and Cooling Holes quantity is 32.Being 262.5mm with axle center spacing bottom tongue-and-groove, tongue-and-groove quantity is 32, tenon
Groove location is corresponding with Cooling Holes.The gap having axial width to be 1mm between rotor scroll dish and stator.
Showing to the result of calculation of existing geometric model numerical simulation, the present embodiment is the base of 20bar at stream pressure
On plinth, the pressure oscillation of larger fluctuation amplitude can be produced.Condition of Pressure Wave is applied to turbine blade film cooling holes Secondary Flow penetrate
In stream, contrasting discovery in the case of voltage stabilizing, the air film hole jet of periodic pressure fluctuation has preferably protection to wall air film
Effect, has more preferable adherent property, the air film in main flow downstream is had persistence and more preferable gas film cooling efficiency.By pressure wave
Dynamic condition is applied in turbo blade internal cooling channel, makes moderate progress the air current flow structure of internal cooling channel, to whole
Body heat transfer effect is significantly improved.The castering action of blade and turbine performance is shown by the application of periodic pressure fluctuation
Write.
Embodiment 2
In the present embodiment, a diameter of 570mm of stator, axial width is 40mm, air current flow space top upper wall surface and axle
Heart distance R3For 270mm.Wherein, air inlet heart distance axle center R5For 130mm, a diameter of 25mm of air inlet, select 16 air inlets
Being uniformly distributed circumferentially, air inlet hole depth is 15mm.Boss is half elliptic, boss centre distance axle center R1For 225mm, two
Angle theta between boss1Being 22.5 °, boss quantity is 16 and is uniformly distributed circumferentially.A diameter of 570mm of rotor scroll dish, axle
It is 40mm to width, top, air current flow space upper wall surface and axle center distance R4For 270mm, a diameter of 50mm of turbine shaft.Wherein,
By pore hole heart distance axle center R2For 225mm, two of which is by angle theta between pore2It is 22.5 °, is 20mm by air vent aperture,
The a length of 40mm in hole, hole number of being bullied is 16 and is uniformly distributed circumferentially.Cooling Holes connects by pore and tongue-and-groove, and Cooling Holes aperture is
10mm, Cooling Holes quantity is 16.Being 262.5mm with axle center spacing bottom tongue-and-groove, tongue-and-groove connects turbine rotor blade, and tongue-and-groove quantity is
16, tongue-and-groove position is corresponding with Cooling Holes.Between rotor scroll dish and stator, gap is less than 2mm.
From the point of view of the result of calculation to existing geometric model numerical simulation, the present embodiment is the base of 20bar at stream pressure
On plinth, the pressure oscillation of relatively minor swing amplitude can be produced.Condition of Pressure Wave is applied to turbine blade film cooling holes Secondary Flow penetrate
In stream, contrasting in the case of voltage stabilizing, the air film hole jet of periodic pressure fluctuation has more preferable protective effect to wall air film
With adherent property, there is more preferable gas film cooling efficiency；The pressure oscillation bigger compared to fluctuation amplitude, the gas that pressure oscillation is less
Fenestra outlet has broader film overcast effect.Condition of Pressure Wave is applied in turbo blade internal cooling channel, right
The air current flow structure of internal cooling channel makes moderate progress, and is significantly improved overall heat exchange effect；Periodic pressure fluctuates
Application notable to the castering action of blade and turbine performance.
Claims (5)
1. a stator part projective table type periodic pressure wave generation device, it is characterised in that: include stator, rotor scroll dish, whirlpool
Wheel rotating shaft, stator and rotor scroll dish are arranged in turbine shaft；Described stator is spill disc structure, according to stator central shaft hole
Circumference is evenly equipped with some identical air inlets, the uniform some identical boss of circumference on stator internal face, and each boss, air inlet
Hole and central shaft hole are radially disposed on same straight line, and boss is identical with air inlet quantity；On described rotor scroll dish, circumference is uniform
Some identical tongue-and-grooves, have radial cooling hole between tongue-and-groove, on rotor scroll Pan Bi, circumference is evenly equipped with some identical by pore,
Each it is connected by Cooling Holes by between pore with corresponding tongue-and-groove, turbine rotor blade is installed between tongue-and-groove；On stator internal face
Boss relative with the hole site of being bullied on rotor scroll dish, between stator and rotor scroll dish formed cooling flow channel.
Stator part projective table type periodic pressure wave generation device the most according to claim 1, it is characterised in that: described stator
On air inlet pass be circular or oval.
Stator part projective table type periodic pressure wave generation device the most according to claim 1, it is characterised in that: described stator
Boss on wall is semicircular arc or half elliptic.
Stator part projective table type periodic pressure wave generation device the most according to claim 1, it is characterised in that: described rotor
It is all circle or ellipse by pore and Cooling Holes pass structure on the turbine disk；By the whirlpool between pore, Cooling Holes and tongue-and-groove
Rotor blades quantity is equal.
Stator part projective table type periodic pressure wave generation device the most according to claim 1, it is characterised in that: stator with turn
Between the sub-turbine disk, axial gap is less than 2mm.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610383125.6A CN106089316A (en) | 2016-06-02 | 2016-06-02 | A kind of stator part projective table type periodic pressure wave generation device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610383125.6A CN106089316A (en) | 2016-06-02 | 2016-06-02 | A kind of stator part projective table type periodic pressure wave generation device |
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| Publication Number | Publication Date |
|---|---|
| CN106089316A true CN106089316A (en) | 2016-11-09 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610383125.6A Pending CN106089316A (en) | 2016-06-02 | 2016-06-02 | A kind of stator part projective table type periodic pressure wave generation device |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108519203A (en) * | 2018-03-14 | 2018-09-11 | 蔡斌奇 | New gas vibrator |
| CN108915785A (en) * | 2018-09-13 | 2018-11-30 | 至玥腾风科技投资集团有限公司 | A kind of turbine disc of on-bladed turbine |
| CN109595039A (en) * | 2019-01-03 | 2019-04-09 | 北京航空航天大学 | A kind of centripetal turbine of gaseous film control structure with seam |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61161407A (en) * | 1985-01-11 | 1986-07-22 | Kansai Electric Power Co Inc:The | Fine gap measuring instrument |
| CN101126326A (en) * | 2007-07-13 | 2008-02-20 | 北京航空航天大学 | Combined cooling structure for turbine blade middle-part round-corner transition impact aerating film |
| CN102135015A (en) * | 2010-01-21 | 2011-07-27 | 施建勇 | Pulse air pressure turbine machine |
| CN102828781A (en) * | 2011-06-16 | 2012-12-19 | 中航商用航空发动机有限责任公司 | Fuel gas turbine cooling blade |
-
2016
- 2016-06-02 CN CN201610383125.6A patent/CN106089316A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS61161407A (en) * | 1985-01-11 | 1986-07-22 | Kansai Electric Power Co Inc:The | Fine gap measuring instrument |
| CN101126326A (en) * | 2007-07-13 | 2008-02-20 | 北京航空航天大学 | Combined cooling structure for turbine blade middle-part round-corner transition impact aerating film |
| CN102135015A (en) * | 2010-01-21 | 2011-07-27 | 施建勇 | Pulse air pressure turbine machine |
| CN102828781A (en) * | 2011-06-16 | 2012-12-19 | 中航商用航空发动机有限责任公司 | Fuel gas turbine cooling blade |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108519203A (en) * | 2018-03-14 | 2018-09-11 | 蔡斌奇 | New gas vibrator |
| CN108915785A (en) * | 2018-09-13 | 2018-11-30 | 至玥腾风科技投资集团有限公司 | A kind of turbine disc of on-bladed turbine |
| CN109595039A (en) * | 2019-01-03 | 2019-04-09 | 北京航空航天大学 | A kind of centripetal turbine of gaseous film control structure with seam |
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