CN106761950A - A kind of hot plate samming is without blending turbine blade cooling device and method - Google Patents
A kind of hot plate samming is without blending turbine blade cooling device and method Download PDFInfo
- Publication number
- CN106761950A CN106761950A CN201710017687.3A CN201710017687A CN106761950A CN 106761950 A CN106761950 A CN 106761950A CN 201710017687 A CN201710017687 A CN 201710017687A CN 106761950 A CN106761950 A CN 106761950A
- Authority
- CN
- China
- Prior art keywords
- hot plate
- samming
- turbo blade
- condensation segment
- blending
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
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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
- 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
- F01D5/182—Transpiration cooling
-
- 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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/288—Protective coatings for blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/203—Heat transfer, e.g. cooling by transpiration cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/20—Heat transfer, e.g. cooling
- F05D2260/205—Cooling fluid recirculation, i.e. after cooling one or more components is the cooling fluid recovered and used elsewhere for other purposes
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Materials Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention provides a kind of hot plate samming without blending turbine blade cooling device and method, including samming hot plate and turbo blade；Samming hot plate includes evaporator section, condensation segment and end cap, and inside turbo blade, in the outer ring of hot plate, steam channel is in the inside of samming hot plate for the woven wire of hot plate for evaporating section.Condensation segment is closed by end cap, and in addition to the wall being connected with turbo blade, remaining wall is all distributed woven wire for condensation segment inner side, and condensation segment outside sets fin；Turbo blade is connected with end cap, and the outer surface of turbo blade is covered by thermal barrier coating；Beneficial effects of the present invention are：Turbine Blade Temperature Field is evenly distributed；Hot plate samming substitutes gaseous film control without Mixing Technology, and the blending of cooling air and high-temperature fuel gas is avoided completely, improves the reliability of engine；Cooling effectiveness is greatly improved, fuel consumption is reduced, the efficiency of engine is improved.
Description
Technical field
The invention belongs to aero engine turbine blades cooling field, it is related to a kind of hot plate samming cold without blending turbo blade
But device and method.
Background technology
Gas-turbine unit is the major impetus device of aviation aircraft, and improving turbine inlet temperature can greatly improve hair
The thrust of motivation simultaneously reduces oil consumption.At present, the lifting speed of turbine front entrance temperature is much larger than high-temperature component material heat resistance
Lifting speed, therefore efficient cooling technology is the key technology for realizing thrust-weight ratio high.
Active service turbo blade is frequently with convection current cooling, impinging cooling, gaseous film control and with answering that thermal barrier coating is combined
Close the type of cooling.Wherein air film cooling technology proposes that the air film cooling technology of turbo blade is in boat in 1870s
Application in air-fuel gas-turbine makes aero-turbine front entrance temperature have larger lifting.Afterwards by numerous effort, whirlpool
Maximum temperature has reached 2012K before wheel.The relevant company of the developed country such as the U.S. and West Europe plans temperature before turbine with research unit
Degree brings up to 2200K~2255K, or even to be up to 2366K to the engine of first use.And the aero-engine of current China
Maximum temperature also only has 1900K before turbine, and it is that China's turbogenerator develops the main of system backwardness that hot-end component is backward in technique
Obstacle.The subject matter of gaseous film control is at present：Gaseous film control can make Turbine Blade Temperature Field uneven, produce larger heat to answer
Power；Cooling gas consumption is continued 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, while meeting turbine
Leaf temperature tends to requirement that is uniform and being blended without cold air and combustion gas, and the present invention is proposed using hot plate samming without blending turbine
The new equipment and method of blade cooling.
The content of the invention
In view of the shortcomings of the prior art, the present invention provide a kind of hot plate samming without blending turbine blade cooling device and
Method, the present invention is cooled down using embedded hot plate according to the structure of turbo blade to turbo blade.
The technical solution adopted in the present invention is：
A kind of hot plate samming is without blending turbine blade cooling device, including samming hot plate and turbo blade two parts.
Described samming hot plate includes evaporator section, condensation segment and end cap, and inside turbo blade, liquid is steaming evaporating section
Hair section vaporization heat absorption, is turbo blade reduction temperature；Condensation segment is closed by end cap, and steam liquefies in condensation segment, is that evaporator section is carried
For endlessly liquid；The woven wire of hot plate in the outer ring of hot plate, equivalent to the liquid-sucking core of hot plate, the liquid of condensation segment
Transport evaporator section, steam channel in the inside of samming hot plate, because liquid is vaporized in evaporator section, the pressure rise of evaporator section,
Under the pressure difference of evaporator section and condensation segment, steam flows to condensation segment by steam channel by evaporator section.Condensation segment except with turbine
Blade connection wall outside, other walls all distribution woven wires, with ensure woven wire under any circumstance can with it is cold
The liquid contact of solidifying section, condensation segment outside sets fin, to increase heat exchange area, improves the heat exchange efficiency of condensation segment, accelerates to steam
The liquefaction of vapour.
Described turbo blade is connected with end cap, and the outer surface of turbo blade is covered by thermal barrier coating, prevents turbo blade
Surfacing melts.
The method cooled down to turbo blade using said apparatus, is comprised the following steps：
High-temperature fuel gas are raised by turbo blade, the temperature of turbo blade, in the woven wire of turbo blade inside hot plate
Liquid heat absorption vaporization, after liquid evaporation volume increase, the pressure rise of evaporator section, then steam by steam channel flow to relatively
The relatively low condensation segment of pressure, steam liquefies in condensation segment, and liquefied liquid is drawn onto evaporator section by woven wire again, so circulation,
Turbo blade is cooled down.
Beneficial effects of the present invention are：1) hot plate samming technique for cooling blades, can make leaf temperature be evenly distributed, reduce because
The thermal stress of the excessive generation of thermograde, so as to extend the service life of blade；2) hot plate samming substitutes air film without Mixing Technology
Cooling, can completely avoid the blending of cooling air and high-temperature fuel gas, and due to aerodynamic loss caused by blending, so that significantly
Improve the reliability of engine；3) hot plate samming can greatly improve cooling effectiveness without Mixing Technology, so as to reduce fuel consumption, carry
The efficiency of engine high.
Brief description of the drawings
Fig. 1 is apparatus of the present invention figure；
In figure：1 steam channel；2 woven wires；3 fins；4 condensation segments；5 end caps；6 evaporator sections.
Specific embodiment
A kind of hot plate samming is without blending turbine blade cooling device, including samming hot plate, turbo blade two parts.Warm
Plate includes evaporator section 6, condensation segment 4 and end cap 5, and evaporator section 6 is in inside turbo blade, and the woven wire 2 of hot plate is in hot plate
Outer ring, equivalent to the liquid-sucking core of hot plate, in the inside of samming hot plate, the outer surface of turbo blade is by thermal barrier coating for steam channel 1
Covering, turbo blade is connected with end cap 5, the condensation segment 4 of end cap closing samming hot plate, and condensation segment with turbo blade except being connected
Outside wall, other walls are all distributed woven wire, and condensation segment outside sets fin 3.
The method cooled down to turbo blade using said apparatus, specially：
High-temperature fuel gas are raised by turbo blade, the temperature of turbo blade, in the woven wire 2 of turbo blade inside hot plate
Liquid heat absorption vaporization, after liquid evaporation volume increase, the pressure rise of evaporator section, then steam phase is flowed to by steam channel 1
The condensation segment 4 relatively low to pressure, steam liquefies in condensation segment 4, and liquefied liquid is drawn onto evaporator section 6 by woven wire 2 again, so
Circulation, cools down to turbo blade.
Claims (3)
1. a kind of hot plate samming is without blending turbine blade cooling device, it is characterised in that described hot plate samming is without blending turbine
Blade cooling device includes samming hot plate and turbo blade；
Described samming hot plate includes evaporator section (6) and condensation segment (4) and end cap (5), and evaporator section (6) is in turbo blade
Portion；End cap (5) is for closing condensation segment (4)；The woven wire (2) of hot plate transports the liquid of condensation segment (4) positioned at hot plate outer ring
It is defeated to evaporator section (6), steam channel (1) is flowed to by evaporator section by steam channel (1) and condensed in the inside of samming hot plate, steam
Section；In addition to the wall being connected with turbo blade, other walls are all distributed woven wire (2) for condensation segment (4) inner side；
Described turbo blade is connected with end cap (5), and the outer surface of turbo blade is covered by thermal barrier coating.
2. a kind of hot plate samming according to claim 1 is without blending turbine blade cooling device, it is characterised in that described
Condensation segment (4) outside sets fin.
3. the method for being cooled down to turbo blade using the device described in claim 1 or 2, it is characterised in that high-temperature fuel gas
By turbo blade, Turbine Blade Temperature Field is raised, the liquid heat absorption vaporization in the woven wire (2) of turbo blade inside hot plate,
Volume increases after liquid evaporation, the pressure rise of evaporator section (6), then to flow to relative pressure by steam channel (1) relatively low for steam
Condensation segment (4), steam liquefies in condensation segment (4), and liquefied liquid is drawn onto evaporator section (6) by woven wire (2) again, and outside sets
Putting the condensation segment (4) of fin (3) increases heat exchange area, and so circulation is cooled down to turbo blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710017687.3A CN106761950B (en) | 2017-01-13 | 2017-01-13 | A kind of hot plate samming is without blending turbine blade cooling device |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710017687.3A CN106761950B (en) | 2017-01-13 | 2017-01-13 | A kind of hot plate samming is without blending turbine blade cooling device |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106761950A true CN106761950A (en) | 2017-05-31 |
| CN106761950B CN106761950B (en) | 2019-03-05 |
Family
ID=58949029
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201710017687.3A Active CN106761950B (en) | 2017-01-13 | 2017-01-13 | A kind of hot plate samming is without blending turbine blade cooling device |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN106761950B (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107687350A (en) * | 2017-08-14 | 2018-02-13 | 大连理工大学 | A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate |
| WO2019033243A1 (en) * | 2017-08-14 | 2019-02-21 | 大连理工大学 | High-efficiency cooling turbine vane apparatus with dual-layered liquid-absorbing core and without opening |
| CN110617114A (en) * | 2019-09-02 | 2019-12-27 | 上海大学 | Ceramic-coated high-temperature alloy stator blade |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2098556U (en) * | 1991-06-01 | 1992-03-11 | 西安交通大学 | Cooling blades of turbine rotor |
| WO2016122483A1 (en) * | 2015-01-28 | 2016-08-04 | Siemens Aktiengesellschaft | Turbine airfoil with trailing edge impingement cooling system |
| WO2016160030A1 (en) * | 2015-04-03 | 2016-10-06 | Siemens Aktiengesellschaft | Turbine airfoil with internal cooling system including features taking advantage of rotating coriolis force |
| CN106089443A (en) * | 2015-04-02 | 2016-11-09 | 通用电气公司 | heat pipe cooling system for turbine |
-
2017
- 2017-01-13 CN CN201710017687.3A patent/CN106761950B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2098556U (en) * | 1991-06-01 | 1992-03-11 | 西安交通大学 | Cooling blades of turbine rotor |
| WO2016122483A1 (en) * | 2015-01-28 | 2016-08-04 | Siemens Aktiengesellschaft | Turbine airfoil with trailing edge impingement cooling system |
| CN106089443A (en) * | 2015-04-02 | 2016-11-09 | 通用电气公司 | heat pipe cooling system for turbine |
| WO2016160030A1 (en) * | 2015-04-03 | 2016-10-06 | Siemens Aktiengesellschaft | Turbine airfoil with internal cooling system including features taking advantage of rotating coriolis force |
Non-Patent Citations (1)
| Title |
|---|
| 郭青青等: "高温热管用于涡轮叶片冷却可行性分析", 《科技信息》 * |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107687350A (en) * | 2017-08-14 | 2018-02-13 | 大连理工大学 | A kind of double-deck liquid-sucking core efficiently cools down turbine guide vane device without perforate |
| WO2019033243A1 (en) * | 2017-08-14 | 2019-02-21 | 大连理工大学 | High-efficiency cooling turbine vane apparatus with dual-layered liquid-absorbing core and without opening |
| CN110617114A (en) * | 2019-09-02 | 2019-12-27 | 上海大学 | Ceramic-coated high-temperature alloy stator blade |
| CN110617114B (en) * | 2019-09-02 | 2021-12-03 | 上海大学 | Ceramic-coated high-temperature alloy stator blade |
Also Published As
| Publication number | Publication date |
|---|---|
| CN106761950B (en) | 2019-03-05 |
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