CN107687350A - A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate - Google Patents
A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate Download PDFInfo
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- CN107687350A CN107687350A CN201710688163.7A CN201710688163A CN107687350A CN 107687350 A CN107687350 A CN 107687350A CN 201710688163 A CN201710688163 A CN 201710688163A CN 107687350 A CN107687350 A CN 107687350A
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- Prior art keywords
- blade
- liquid
- double
- sucking core
- guide vane
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Classifications
-
- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/08—Cooling; Heating; Heat-insulation
- F01D25/12—Cooling
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device, including dividing plate outer shroud, turbo blade, stationary blade carrier, fin, double-deck liquid-sucking core hot plate without perforate；Turbo blade is arranged between dividing plate outer shroud and stationary blade carrier, and stationary blade carrier upper surface and turbo blade internal run-through, lower surface penetrates with fin.Turbo blade includes thermal barrier coating and metal blade wall, and thermal barrier coating is coated in the outer surface of metal blade wall, and double-deck liquid-sucking core is attached to metal blade wall inner surface.Turbo blade is evaporator section, and stationary blade carrier is condensation segment.The present invention makes cooling blade keeping temperature be evenly distributed, and reduces the thermal stress caused by the temperature difference, extends blade service life；The blending of cooling air and high-temperature fuel gas is avoided, and due to aerodynamic loss caused by blending, improves engine reliability；The entrainment limit and capillary limitation of double-deck liquid sucting core structure increase hot plate structure；Blade ensures blades integrity, improves blade mechanism intensity without perforate；Cooling effectiveness is improved, reduces fuel consumption, improves engine efficiency.
Description
Technical field
The invention belongs to aero engine turbine blades cooling field, is related to a kind of double-deck liquid-sucking core and is efficiently cooled down without perforate
Turbine guide vane device.
Background technology
Gas-turbine unit is the major impetus device of aviation aircraft, and hair can be greatly improved by improving turbine inlet temperature
The thrust of motivation simultaneously reduces oil consumption.At present, the lifting speed of turbine front entrance temperature is about 20K/, and high-temperature component material is resistance to
The lifting speed of warm nature energy is about 8K/, therefore efficient cooling technology is the key for realizing high thrust-weight ratio.
Active service turbo blade is frequently with answering with convection current cooling, impinging cooling, gaseous film control and with what thermal barrier coating was combined
Close the type of cooling.Wherein air film cooling technology proposes in nineteen seventies, and the air film cooling technology of turbo blade is navigating
Application in air-fuel gas-turbine makes aero-turbine front entrance temperature have larger lifting.Pass through numerous effort, whirlpool afterwards
Maximum temperature reaches 2012K before wheel.The relevant company of the developed country such as the U.S. and West Europe plans with research unit will be warm before turbine
Degree brings up to 2200K~2255K, or even to be up to 2366K to the engine of first use.And the aero-engine in current China
Maximum temperature also only has 1900K before turbine, and hot-end component backward in technique is that China's turbogenerator develops the main of system backwardness
Reason.The subject matter of gaseous film control is at present：Gaseous film control can make Turbine Blade Temperature Field uneven, and producing larger heat should
Power；Cooling gas dosage continues to increase so that flowing is more complicated with flow field structure in leaf grating runner；The presence of spray-hole and seam
So that blade is difficult to keep integrality, it is easy to cause mechanical problem.
To realize the further cooling to turbo blade, maximum temperature is further lifted before making turbine, is considered as hot plate
Turbo blade is cooled down, hot plate is a kind of efficient cooling device, and the Cooling Technique Based On Thermal Driving of hot plate built in applying,
Its key issue is that can hot plate have enough an entrainment limit and capillary limitation, and the present invention proposes a kind of based on hot plate principle
Double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate.
The content of the invention
For insufficient existing for existing air film cooling technology, the present invention proposes that a kind of double-deck liquid-sucking core efficiently cools down without perforate
Turbine guide vane device, the cooling turbine guide vane device are based on hot plate principle.The present invention is according to turbo blade and the knot of internal hot plate
Structure, blade is cooled down using the hot plate of built-in double-deck liquid-sucking core.
The technical solution adopted in the present invention is：
A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device, including turbine guide vane device and double-deck liquid-sucking core without perforate
Hot plate two parts.
Described turbine guide vane device includes dividing plate outer shroud 1, turbo blade 2, stationary blade carrier 3, fin 4, wherein, turbine leaf
Piece 2 is evaporator section, and stationary blade carrier 3 is condensation segment, and liquid vaporizes in evaporator section to absorb heat, and reduces the temperature of turbo blade 2, steam is cold
Solidifying section liquefaction, endlessly liquid is provided for evaporator section.Described dividing plate outer shroud 1 is fixed on the upper surface of turbo blade 2, rises
Fixation.Described fin 4 is cuboid groove structure.
Described stationary blade carrier 3 is hollow structure, and the upper surface of stationary blade carrier 3 is provided with opening, rims and turbo blade 2
Lower surface fix, stationary blade carrier 3 is connected by the inside of upper surface open and turbo blade 2, for passing through steam；Stationary blade carrier
3 lower surfaces are equidistantly provided with multiple strip openings, and fin 4 is arranged at the strip aperture position, and the two passes through strip opening
Insertion, i.e. fin 4 are cuboid, and equidistant arrangement, for increasing condensation segment and extraneous heat exchange area, increases on stationary blade carrier 3
Strong heat exchange.Filling liquid cooling working medium in the inside of stationary blade carrier 3 and fin 4, for providing cooling liquid, steam is condensed into herein
Liquid.The equidistant arrangement of turbo blade 2 is on stationary blade carrier 3.
Described turbo blade 2 includes thermal barrier coating 8 and metal blade wall 7, and metal blade wall 7 is hollow structure, hollow
Part forms steam channel 5.Thermal barrier coating 8 is coated in the outer surface of metal blade wall 7, prevents the surfacing of metal blade wall 7
Fusing；Metal blade wall 7 is without open-celled structure, keeps blades integrity, the problems such as avoiding causing mechanical strength, and can keep away
Exempt from cooling gas and aerodynamic loss caused by main flow gas mixing.
Described double-deck liquid-sucking core is located inside turbo blade 2, is attached to the inner surface of metal blade wall 7, and described is double
Layer liquid-sucking core 6 includes layer of metal felt 9 and layer of metal silk screen 10, and metal felt 9 is attached to the inner surface of metal blade wall 7, metal
Silk screen 10 is attached on metal felt 9.Both metal felt 9 and woven wire 10 have different fibre diameter and porosity, can
The preferably entrainment limit and capillary limitation of lifting hot plate structure, avoid liquid-sucking core carrying of liquids deficiency or to lifting liquid height
Not enough blade surface is caused sufficiently to cool down；The fibre diameter of described metal felt 9 is 6~20 μm, porosity 0.5
~0.9；The fibre diameter of woven wire 10 is 6~20 μm, and porosity is 0.3~0.7.
Described dividing plate outer shroud 1 and turbo blade 2 and the material of stationary blade carrier 3 are Titanium Alloys for Aviation, nickel base superalloy
Deng.The described material of fin 4 is aluminium alloy, stainless steel etc..The described material of thermal barrier coating 8 is zirconium oxide etc..Described liquid
Cooling down working medium includes Liquid Sodium, liquid lithium, liquid potassium.
The present invention the course of work be：High-temperature fuel gas contacts with turbo blade 2, the temperature rise of turbo blade 2；Now,
Liquid cooled working medium in stationary blade carrier 3 is transported turbine leaf by the double-deck liquid-sucking core 6 inside turbo blade 2 by capillary force
Piece 2, liquid cooled working medium absorbs the heat of turbo blade 2 in double-deck liquid-sucking core 6, and the steam after heat absorption vaporization is directly entered steam
In passage 5, volume increases after the evaporation of liquid cooled working medium, and the pressure rise at evaporator section turbo blade 2, steam is led to by steam
Road 5 flows to the relatively low condensation segment of relative pressure, and because steam channel 5 connects with stationary blade carrier 3, steam liquefies in condensation segment, liquid
Change liberated heat and outside is transmitted to by fin 4, the liquid after liquefaction is drawn onto evaporation by double-deck liquid-sucking core 6 by capillary force again
Section, so circulation, are cooled down to turbo blade 2.
Beneficial effects of the present invention are：1) cooling blade keeping temperature is evenly distributed, reduce hot because of caused by the temperature difference
Stress, so as to extend the service life of blade；2) blending of cooling air and high-temperature fuel gas is avoided, and due to caused by blending
Aerodynamic loss, improve the reliability of engine；3) blade ensures blades integrity, improves the mechanical strength of blade without perforate；4)
Double-deck liquid sucting core structure, increase the entrainment limit and capillary limitation of hot plate structure；5) cooling effectiveness is increased substantially, reduces combustion
Material consumption, improves engine efficiency.
Brief description of the drawings
Fig. 1 is apparatus of the present invention overall diagram；
Fig. 2 is apparatus of the present invention turbine blade arrangement figure；
Fig. 3 is apparatus of the present invention bilayer liquid sucting core structure figure；
Fig. 4 is the structure chart of stationary blade carrier；
In figure：1 dividing plate outer shroud；2 turbo blades；3 stationary blade carriers；4 fins；5 steam channels；6 double-deck liquid-sucking cores；7 metals
Blade wall；8 thermal barrier coatings；9 metal felts；10 woven wires.
Embodiment
Below in conjunction with specific embodiment, the present invention will be further described.
A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device, including turbine guide vane device and double-deck liquid-sucking core without perforate
Hot plate.Described turbine guide vane device includes dividing plate outer shroud 1, turbo blade 2, stationary blade carrier 3, fin 4, wherein, turbo blade 2
For evaporator section, stationary blade carrier 3 is condensation segment.Described dividing plate outer shroud 1 is fixed on the upper surface of turbo blade 2.Described fin 4
For cuboid groove structure.Described stationary blade carrier 3 is hollow structure, and the upper surface of stationary blade carrier 3 is provided with opening, rims with
The lower surface of turbo blade 2 is fixed, and stationary blade carrier 3 is connected by upper surface open with the inside of turbo blade 2, is steamed for passing through
Vapour；The lower surface of stationary blade carrier 3 is equidistantly provided with multiple strip openings, is connected with fin 4, and the two is penetrated by strip opening,
Fin 4 is used to increase condensation segment and extraneous heat exchange area.Filling liquid cooling working medium liquid in the inside of stationary blade carrier 3 and fin 4
State sodium, for steam to be condensed into liquid.Described turbo blade 2 includes thermal barrier coating 8 and metal blade wall 7, metal blade
Wall 7 is hollow structure, and hollow space forms steam channel 5.Thermal barrier coating 8 is coated in the outer surface of metal blade wall 7, prevents gold
Belong to the fusing of the surfacing of blade wall 7；Metal blade wall 7 is without open-celled structure.Described double-deck liquid-sucking core is located in turbo blade 2
Portion, is attached to the inner surface of metal blade wall 7, and described double-deck liquid-sucking core 6 includes layer of metal felt 9 and layer of metal silk screen
10, metal felt 9 is attached to the inner surface of metal blade wall 7, and woven wire 10 is attached on metal felt 9.Dividing plate outer shroud 1, turbine leaf
Piece 2, the material of stationary blade carrier 3 are Titanium Alloys for Aviation, and the material of fin 4 is aluminium alloy, and the material of thermal barrier coating 8 is zirconium oxide.
Claims (8)
1. a kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate, it is characterised in that described double-deck liquid-sucking core without
Perforate, which efficiently cools down turbine guide vane device, includes turbine guide vane device and double-deck liquid-sucking core hot plate；
Described turbine guide vane device includes dividing plate outer shroud (1), turbo blade (2), stationary blade carrier (3), fin (4), wherein, whirlpool
Impeller blade (2) is evaporator section, and stationary blade carrier (3) is condensation segment；Described dividing plate outer shroud (1) is fixed on the upper of turbo blade (2)
Surface；Described fin (4) is cuboid groove structure；
Described stationary blade carrier (3) is hollow structure, and stationary blade carrier (3) upper surface is provided with opening, rims and turbo blade
(2) lower surface is fixed, and stationary blade carrier (3) is connected by upper surface open with turbo blade (2) inside, for passing through steam；
Stationary blade carrier (3) lower surface is equidistantly provided with multiple strip openings, is connected with fin (4), and the two is penetrated by strip opening,
Fin (4) is used to increase condensation segment and extraneous heat exchange area；Stationary blade carrier (3) is internal and the interior filling liquid of fin (4) cools down
Working medium, for providing cooling liquid, steam is condensed into liquid herein；
Described turbo blade (2) includes thermal barrier coating (8) and metal blade wall (7), and metal blade wall (7) is hollow structure,
Hollow space forms steam channel (5)；Thermal barrier coating (8) is coated in the outer surface of metal blade wall (7), prevents metal blade wall
(7) surfacing melts；Metal blade wall (7) is without open-celled structure；
Described double-deck liquid-sucking core is located at turbo blade (2) inside, is attached to the inner surface of metal blade wall (7), and described is double
Layer liquid-sucking core (6) includes metal felt (9) and woven wire (10), and metal felt (9) is attached to metal blade wall (7) inner surface, gold
Category silk screen (10) is attached on metal felt (9)；Both described metal felt (9) and woven wire (10) have different fibers straight
Footpath and porosity, the fibre diameter of metal felt (9) is 6~20 μm, and porosity is 0.5~0.9；The fiber of woven wire (10) is straight
Footpath is 6~20 μm, and porosity is 0.3~0.7；
The present invention the course of work be：High-temperature fuel gas contacts with turbo blade (2), the temperature rise of turbo blade (2)；Turbine leaf
Liquid cooled working medium in stationary blade carrier (3) is transported turbine leaf by the internal double-deck liquid-sucking core (6) of piece (2) by capillary force
Piece (2), the double-deck interior liquid cooled working medium of liquid-sucking core (6) absorb the heat of turbo blade (2), and the steam after heat absorption vaporization directly enters
Enter in steam channel (5), volume increase, the pressure rise at evaporator section turbo blade (2) place, steam after the evaporation of liquid cooled working medium
The relatively low condensation segment of relative pressure is flowed to by steam channel (5), because steam channel (5) connects with stationary blade carrier (3), steam
Liquefied in condensation segment, liquefaction liberated heat is transmitted to outside by fin (4), and the liquid after liquefaction is again by double-deck liquid-sucking core (6)
Evaporator section is drawn onto by capillary force, so circulation, turbo blade (2) is cooled down.
2. a kind of double-deck liquid-sucking core according to claim 1 efficiently cools down turbine guide vane device without perforate, it is characterised in that
Described liquid cooled working medium includes Liquid Sodium, liquid lithium, liquid potassium.
3. a kind of double-deck liquid-sucking core according to claim 1 or 2 efficiently cools down turbine guide vane device without perforate, its feature exists
In described dividing plate outer shroud (1), turbo blade (2), the material of stationary blade carrier (3) are Titanium Alloys for Aviation, nickel-base high-temperature closes
Gold.
4. a kind of double-deck liquid-sucking core according to claim 1 or 2 efficiently cools down turbine guide vane device without perforate, its feature exists
In described fin (4) material is aluminium alloy, stainless steel.
5. a kind of double-deck liquid-sucking core according to claim 3 efficiently cools down turbine guide vane device without perforate, it is characterised in that
Described fin (4) material is aluminium alloy, stainless steel.
6. a kind of double-deck liquid-sucking core according to claim 1 or 2 or 5 efficiently cools down turbine guide vane device without perforate, it is special
Sign is that described thermal barrier coating (8) material is zirconium oxide.
7. a kind of double-deck liquid-sucking core according to claim 3 efficiently cools down turbine guide vane device without perforate, it is characterised in that
Described thermal barrier coating (8) material is zirconium oxide.
8. a kind of double-deck liquid-sucking core according to claim 4 efficiently cools down turbine guide vane device without perforate, it is characterised in that
Described thermal barrier coating (8) material is zirconium oxide.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710688163.7A CN107687350A (en) | 2017-08-14 | 2017-08-14 | A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710688163.7A CN107687350A (en) | 2017-08-14 | 2017-08-14 | A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate |
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| CN107687350A true CN107687350A (en) | 2018-02-13 |
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| CN201710688163.7A Pending CN107687350A (en) | 2017-08-14 | 2017-08-14 | A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110486099A (en) * | 2019-07-22 | 2019-11-22 | 西北工业大学 | A kind of high-temperature heat pipe turbo blade thermal protection structure |
| CN111010847A (en) * | 2019-11-22 | 2020-04-14 | 广东工业大学 | Soaking plate type heat dissipation device |
| US10877062B2 (en) | 2018-05-09 | 2020-12-29 | Rosemount Aerospace Inc. | Aft-located heated ramp for ice and water management of angle of attack sensors |
| US10928416B2 (en) | 2018-05-09 | 2021-02-23 | Rosemount Aerospace Inc. | Dual heated ramp for ice and water management in angle of attack sensors |
| US11142323B2 (en) | 2018-01-05 | 2021-10-12 | Rosemount Aerospace Inc. | Features to prevent ice accumulation on heated faceplate |
| US11162970B2 (en) | 2019-06-17 | 2021-11-02 | Rosemount Aerospace Inc. | Angle of attack sensor |
| US11181545B2 (en) | 2017-08-17 | 2021-11-23 | Rosemount Aerospace Inc. | Angle of attack sensor with thermal enhancement |
| US11649057B2 (en) | 2019-12-13 | 2023-05-16 | Rosemount Aerospace Inc. | Static plate heating arrangement |
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| JP2007240075A (en) * | 2006-03-09 | 2007-09-20 | Matsushita Electric Ind Co Ltd | Heat transport device, and liquid cooling system using the same |
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Cited By (10)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US11181545B2 (en) | 2017-08-17 | 2021-11-23 | Rosemount Aerospace Inc. | Angle of attack sensor with thermal enhancement |
| US11768219B2 (en) | 2017-08-17 | 2023-09-26 | Rosemount Aerospace Inc. | Angle of attack sensor with thermal enhancement |
| US11142323B2 (en) | 2018-01-05 | 2021-10-12 | Rosemount Aerospace Inc. | Features to prevent ice accumulation on heated faceplate |
| US10877062B2 (en) | 2018-05-09 | 2020-12-29 | Rosemount Aerospace Inc. | Aft-located heated ramp for ice and water management of angle of attack sensors |
| US10928416B2 (en) | 2018-05-09 | 2021-02-23 | Rosemount Aerospace Inc. | Dual heated ramp for ice and water management in angle of attack sensors |
| US11162970B2 (en) | 2019-06-17 | 2021-11-02 | Rosemount Aerospace Inc. | Angle of attack sensor |
| CN110486099A (en) * | 2019-07-22 | 2019-11-22 | 西北工业大学 | A kind of high-temperature heat pipe turbo blade thermal protection structure |
| CN111010847A (en) * | 2019-11-22 | 2020-04-14 | 广东工业大学 | Soaking plate type heat dissipation device |
| CN111010847B (en) * | 2019-11-22 | 2021-09-07 | 广东工业大学 | Soaking plate type heat dissipation device |
| US11649057B2 (en) | 2019-12-13 | 2023-05-16 | Rosemount Aerospace Inc. | Static plate heating arrangement |
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Application publication date: 20180213 |