CN109538304A - A kind of miniature turbo blade combination cooling structure that staggeredly rib is combined with air film hole - Google Patents

A kind of miniature turbo blade combination cooling structure that staggeredly rib is combined with air film hole Download PDF

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Publication number
CN109538304A
CN109538304A CN201811355431.4A CN201811355431A CN109538304A CN 109538304 A CN109538304 A CN 109538304A CN 201811355431 A CN201811355431 A CN 201811355431A CN 109538304 A CN109538304 A CN 109538304A
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China
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rib
cooling
staggeredly
air film
blade
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CN201811355431.4A
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CN109538304B (en
Inventor
栾刚
栾一刚
殷越
马鸿飞
孙海鸥
王忠义
孙涛
王松
万雷
杨连峰
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Harbin Engineering University
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Harbin Engineering University
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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
    • F01D5/186—Film 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
    • F01D5/14—Form or construction
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • 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
    • F01D5/187—Convection 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
    • F01D5/14—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
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • 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
    • F01D9/06—Fluid supply conduits to nozzles or the like
    • F01D9/065—Fluid supply or removal conduits traversing the working fluid flow, e.g. for lubrication-, cooling-, or sealing fluids
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/22—Manufacture essentially without removing material by sintering
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/23—Manufacture essentially without removing material by permanently joining parts together
    • F05D2230/232—Manufacture essentially without removing material by permanently joining parts together by welding
    • F05D2230/234—Laser welding
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/30—Manufacture with deposition of material
    • F05D2230/31—Layer deposition
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/313—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being perpendicular to each other
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/31—Arrangement of components according to the direction of their main axis or their axis of rotation
    • F05D2250/314—Arrangement of components according to the direction of their main axis or their axis of rotation the axes being inclined in relation to each other
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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
    • F05D2260/201—Heat transfer, e.g. cooling by impingement of a fluid
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence
    • 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
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

The purpose of the present invention is to provide a kind of miniature turbo blade combination cooling structures that staggeredly rib is combined with air film hole, including blade body, side is respectively pressure face, suction surface before and after blade body, blade body blade root is cooling gas inlet, cooling tapered channels are set in blade body and serpentine channel is arranged by partition, it is separated by between cooling tapered channels and serpentine channel by inner wall, the rib of column is set in cooling tapered channels, the rib cooling duct that interlocks is set in serpentine channel, the rib that interlocks staggeredly is set in rib cooling duct.Minitype channel of the present invention improves internal heat transfer surface area, and staggeredly rib has compared with high heat-exchanging performance, staggeredly has micro-hole inside rib, forms gaseous film control channel, reduces thermal stress.

Description

A kind of miniature turbo blade combination cooling structure that staggeredly rib is combined with air film hole
Technical field
The present invention relates to a kind of turbo blades, specifically turbine blade cooling structure.
Background technique
Gas turbine have light weight, small in size, single-machine capacity are big, starting is fast, pollution less, the thermal efficiency is high, good economy performance The features such as.By the simple cycle mode of gas turbine it is found that improving specific power and performance by way of improving combustion gas initial temperature. The location of turbo blade temperature is high, stress is complicated, working environment is severe, therefore the work that can turbo blade safe and reliable It is most important for the operation of engine.The performance indexes of blade becomes the important finger of measured engine development degree The ability that mark, especially turbo blade can bear high temperature.In short, the development level of turbo blade, which becomes, measures a country The important symbol of gas turbine development level.
Currently, temperature is more than the bearing temperature of its material already before turbine blade of gas turbine.Guarantee that blade can be safe It reliably works, is mainly realized by two approach, first is that the high temperature resistance of material is improved, second is that more using cooling capacity The strong type of cooling reduces the temperature of blade.From the point of view of existing data, in the past few decades, turbine inlet temperature mentions every year on average Rise 22K, wherein 70% is because using the mode that is more efficiently cooled, and 30% is because component materials heat resistance mentions Rise the development with production technology.With the development of the type of cooling, the introducing of new heat transfer heat transfer mechanism, turbine inlet temperature will gradually It improves.
Advanced gas turbine design is improved efficiency by improving combustion gas initial temperature, is by developing resistance to height in the past Adiabator and cooling technology improve combustion gas initial temperature, it is ensured that turbine material can meet intensity requirement and make under high-temperature fuel gas Use the service life.The usage amount of cooling air is more, bigger to the wasted work of compressor, therefore reduces the drag losses of cooling air, Compressor acting is reduced, gas turbine efficiency is improved.Nowadays, it not only to improve efficiency, also to reduce pollution of the combustion gas to environment, therefore Air is generated from compressor, needs more to enter combustion chamber and participates in burning, reducing pollutant must discharge.Therefore, for cooling down Air will reduce.The reduction of air capacity will bring challenges for the design of the cooling structure of turbine.
Nowadays the type of cooling mainly used has, impinging cooling, convection current cooling, gaseous film control, diverging cooling.Gaseous film control It is that one layer of temperature is formed outside turbo blade is lower by coupled air film hole for the cooling gas of internal cooling channel Air film, to completely cut off a kind of external type of cooling of high-temperature fuel gas.Gaseous film control is distributed in each position of blade, therefore is had It plays an important role.
Summary of the invention
The purpose of the present invention is to provide a kind of miniature friendships for further increasing cooling effect, improving blade heat-resisting ability The turbo blade combination cooling structure that wrong rib is combined with air film hole.
The object of the present invention is achieved like this:
A kind of miniature turbo blade combination cooling structure that staggeredly rib is combined with air film hole of the invention, it is characterized in that: packet Blade body is included, side is respectively pressure face, suction surface before and after blade body, and blade body blade root is cooling gas inlet, is set in blade body It sets cooling tapered channels and serpentine channel is arranged by partition, be separated by between cooling tapered channels and serpentine channel by inner wall, The rib of column is set in cooling tapered channels, the rib cooling duct that interlocks is set in serpentine channel, is staggeredly arranged in rib cooling duct and interlocks Rib.
The present invention may also include:
1, the staggeredly rib is 3D kagome structure.
It 2, is miniature air film hole inside the staggeredly rib, miniature air film hole leads to outside blade body, passes through miniature air film hole The gas flowed to outside blade body forms air film outside blade body.
Present invention has an advantage that
1, minitype channel improves internal heat transfer surface area.
2, the rib that interlocks is with the cooling structure compared with high heat-exchanging performance.
3, interlock rib inside with micro-hole, form gaseous film control channel.
4, this structure reduces thermal stress.
Detailed description of the invention
Fig. 1 a is sectional view of the invention, and Fig. 1 b is A sectional view；
Fig. 2 is the rib air film hole mixed structure schematic diagram that interlocks；
Fig. 3 is that blade inner wall interlocks rib air inlet；
Fig. 4 is staggered rib passage schematic three dimensional views；
Fig. 5 is staggered rib passage and air film hole cooling air-flow schematic diagram.
Specific embodiment
It illustrates with reference to the accompanying drawing and the present invention is described in more detail:
In conjunction with Fig. 1-5, the turbo blade combination cooling structure that the present invention is combined with the miniature rib structure that interlocks with air film, It mainly include all purpose turbine blade interior serpentine channel cooling structure, the staggeredly rib with miniature air film hole, and with staggeredly The cooling duct of rib.Serpentine channel cooling structure inside turbo blade, this structure can improve blade heat exchange property.Cooling gas is logical Transmission channel is crossed to enter from serpentine channel close to the external cooling duct with staggeredly rib, portion gas by the rib that interlocks inside Miniature air film hole flow to blade exterior formed air film.
Cooling air is entered the cooling duct of blade interior by blade root, and part cooling air flows through tail edge area domain and has The cooling tapered channels of the rib of column 3.Remaining gas enters with staggeredly rib cooling duct and serpentine channel.After gas enters, two Cooling duct is separated by by inner wall, and air-flow is divided into two parts, cools down the suction surface 1 of blade, pressure face 2, both for outer respectively Wall.Such as Fig. 4, staggeredly rib is in 3D kagome structure, and cooling gas flows through the cooling duct, strengthens wall surface heat exchange.Such as Fig. 5, handing over After the cooling air of wrong rib cooling duct flows through staggeredly rib, Convective heat tranfer cooling is carried out to blade outside wall surface, is subsequently flowed into snakelike Cooling duct；The cooling air of serpentine channel passes through aperture Fig. 3 of inner wall, and into inside staggeredly rib, subsequent cooling air passes through The air film hole of blade outside wall surface flows out, and forms cooling air film in blade exterior.
A kind of miniature turbo blade combination cooling structure that staggeredly rib is combined with air film hole of the invention, it is cold in blade snake shape But channel interior has staggeredly rib cooling duct.Staggeredly there is in rib smaller aperture, communicated with blade air film hole.Staggeredly rib is cooling Channel middle rib is in 3D kagome structure.Staggered rib passage and serpentine channel are separated by by inner wall, and inner wall has venthole, stomata It is communicated with exterior vent.

Claims (3)

1. a kind of miniature turbo blade combination cooling structure that staggeredly rib is combined with air film hole, it is characterized in that: include blade body, Side is respectively pressure face, suction surface before and after blade body, and blade body blade root is cooling gas inlet, and it is tapered that cooling is arranged in blade body Simultaneously serpentine channel is arranged by partition in channel, is separated by between cooling tapered channels and serpentine channel by inner wall, cooling tapered logical The rib of column is set in road, the rib cooling duct that interlocks is set in serpentine channel, the rib that interlocks staggeredly is set in rib cooling duct.
2. the miniature turbo blade combination cooling structure that staggeredly rib is combined with air film hole of one kind according to claim 1, It is characterized in that: the staggeredly rib is 3D kagome structure.
3. the miniature turbo blade combination cooling knot that staggeredly rib is combined with air film hole of one kind according to claim 1 or 2 Structure, it is characterized in that: being miniature air film hole inside the staggeredly rib, miniature air film hole leads to outside blade body, passes through miniature air film The gas that hole flows to outside blade body forms air film outside blade body.
CN201811355431.4A 2018-11-14 2018-11-14 Turbine blade mixed cooling structure combining micro staggered ribs and air film holes Active CN109538304B (en)

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109882247A (en) * 2019-04-26 2019-06-14 哈尔滨工程大学 One kind having venthole inner wall multi-channel internal cooling gas turbine turbo blade
CN110043327A (en) * 2019-04-26 2019-07-23 哈尔滨工程大学 A kind of discontinuous rib inside cooling structure for turbine blade of gas turbine
CN111120009A (en) * 2019-12-30 2020-05-08 中国科学院工程热物理研究所 Ribbed transverse flow channel with rows of film holes having channel-shaped cross-sections
CN113107610A (en) * 2021-04-13 2021-07-13 西北工业大学 Through seam type semi-split seam trailing edge cooling structure and turbine blade
CN113107608A (en) * 2021-04-13 2021-07-13 西北工业大学 A vortex screw hole cooling structure and turbine blade for turbine blade trailing edge
CN113236370A (en) * 2021-05-25 2021-08-10 杭州汽轮动力集团有限公司 Cooling structure of high-pressure moving blade of turbine of gas turbine
CN113669756A (en) * 2021-08-31 2021-11-19 西北工业大学 Double-layer double-effect heat insulation wall for afterburner cavity and double-effect cooling method
US11965428B1 (en) 2022-10-28 2024-04-23 Doosan Enerbility Co., Ltd. Airfoil cooling structure, airfoil having airfoil cooling structure, and turbine blade/vane element including airfoil

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JPH0223201A (en) * 1988-07-13 1990-01-25 Toshiba Corp Turbine blade
KR20020069462A (en) * 2001-02-27 2002-09-04 조형희 Discrete rib arrangements in turbine blade cooling passage
US7713027B2 (en) * 2006-08-28 2010-05-11 United Technologies Corporation Turbine blade with split impingement rib
CN101910564A (en) * 2008-01-08 2010-12-08 株式会社Ihi The cooling construction of turbine blade
US8182224B1 (en) * 2009-02-17 2012-05-22 Florida Turbine Technologies, Inc. Turbine blade having a row of spanwise nearwall serpentine cooling circuits
CN203584471U (en) * 2013-12-12 2014-05-07 中航商用航空发动机有限责任公司 Abnormal shaped film hole structure and turbine blade
WO2014105113A1 (en) * 2012-12-28 2014-07-03 United Technologies Corporation Gas turbine engine component having vascular engineered lattice structure
CN103967621A (en) * 2014-04-08 2014-08-06 上海交通大学 Cooling device with small inclined rib-dimple composite structure
CN106930788A (en) * 2015-10-15 2017-07-07 通用电气公司 Turbo blade
CN107835887A (en) * 2015-07-13 2018-03-23 西门子公司 Blade and its manufacture method for fluid dynamic machinery
CN108369930A (en) * 2015-11-11 2018-08-03 全南大学校产学协力团 Three-dimensional heat sink
US10100646B2 (en) * 2012-08-03 2018-10-16 United Technologies Corporation Gas turbine engine component cooling circuit

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH0223201A (en) * 1988-07-13 1990-01-25 Toshiba Corp Turbine blade
KR20020069462A (en) * 2001-02-27 2002-09-04 조형희 Discrete rib arrangements in turbine blade cooling passage
US7713027B2 (en) * 2006-08-28 2010-05-11 United Technologies Corporation Turbine blade with split impingement rib
CN101910564A (en) * 2008-01-08 2010-12-08 株式会社Ihi The cooling construction of turbine blade
US8182224B1 (en) * 2009-02-17 2012-05-22 Florida Turbine Technologies, Inc. Turbine blade having a row of spanwise nearwall serpentine cooling circuits
US10100646B2 (en) * 2012-08-03 2018-10-16 United Technologies Corporation Gas turbine engine component cooling circuit
WO2014105113A1 (en) * 2012-12-28 2014-07-03 United Technologies Corporation Gas turbine engine component having vascular engineered lattice structure
CN203584471U (en) * 2013-12-12 2014-05-07 中航商用航空发动机有限责任公司 Abnormal shaped film hole structure and turbine blade
CN103967621A (en) * 2014-04-08 2014-08-06 上海交通大学 Cooling device with small inclined rib-dimple composite structure
CN107835887A (en) * 2015-07-13 2018-03-23 西门子公司 Blade and its manufacture method for fluid dynamic machinery
CN106930788A (en) * 2015-10-15 2017-07-07 通用电气公司 Turbo blade
CN108369930A (en) * 2015-11-11 2018-08-03 全南大学校产学协力团 Three-dimensional heat sink

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN109882247A (en) * 2019-04-26 2019-06-14 哈尔滨工程大学 One kind having venthole inner wall multi-channel internal cooling gas turbine turbo blade
CN110043327A (en) * 2019-04-26 2019-07-23 哈尔滨工程大学 A kind of discontinuous rib inside cooling structure for turbine blade of gas turbine
CN109882247B (en) * 2019-04-26 2021-08-20 哈尔滨工程大学 Multi-channel internal cooling gas turbine blade with air vent inner wall
CN111120009A (en) * 2019-12-30 2020-05-08 中国科学院工程热物理研究所 Ribbed transverse flow channel with rows of film holes having channel-shaped cross-sections
CN111120009B (en) * 2019-12-30 2022-06-07 中国科学院工程热物理研究所 Ribbed transverse flow channel with rows of film holes having channel-shaped cross-sections
CN113107610A (en) * 2021-04-13 2021-07-13 西北工业大学 Through seam type semi-split seam trailing edge cooling structure and turbine blade
CN113107608A (en) * 2021-04-13 2021-07-13 西北工业大学 A vortex screw hole cooling structure and turbine blade for turbine blade trailing edge
CN113236370A (en) * 2021-05-25 2021-08-10 杭州汽轮动力集团有限公司 Cooling structure of high-pressure moving blade of turbine of gas turbine
CN113669756A (en) * 2021-08-31 2021-11-19 西北工业大学 Double-layer double-effect heat insulation wall for afterburner cavity and double-effect cooling method
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