CN109538304B - Turbine blade mixed cooling structure combining micro staggered ribs and air film holes - Google Patents

Turbine blade mixed cooling structure combining micro staggered ribs and air film holes Download PDF

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Publication number
CN109538304B
CN109538304B CN201811355431.4A CN201811355431A CN109538304B CN 109538304 B CN109538304 B CN 109538304B CN 201811355431 A CN201811355431 A CN 201811355431A CN 109538304 B CN109538304 B CN 109538304B
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cooling
staggered
channel
rib
blade
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CN109538304A (en
Inventor
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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    • 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

Abstract

The invention aims to provide a turbine blade mixed cooling structure combining a miniature staggered rib and a gas film hole, which comprises a blade body, wherein the front side and the rear side of the blade body are respectively a pressure surface and a suction surface, the blade root of the blade body is a cooling gas inlet, a cooling tapered channel is arranged in the blade body, a serpentine channel is arranged through a partition plate, the cooling tapered channel and the serpentine channel are separated by an inner wall, a column rib is arranged in the cooling tapered channel, a staggered rib cooling channel is arranged in the serpentine channel, and a staggered rib is arranged in the staggered rib cooling channel. The micro channel improves the internal heat exchange area, the staggered ribs have higher heat exchange performance, and the micro holes are formed in the staggered ribs to form the air film cooling channel, so that the thermal stress is reduced.

Description

Turbine blade mixed cooling structure combining micro staggered ribs and air film holes
Technical Field
The invention relates to a turbine blade, in particular to a turbine blade cooling structure.
Background
The gas turbine has the characteristics of light weight, small volume, large single machine power, quick start, less pollution, high thermal efficiency, good economy and the like. The simple cycle method of the gas turbine is known to improve the specific power and the performance by increasing the initial temperature of the gas. The turbine blade is in a position with high temperature, complex stress and severe working environment, so whether the turbine blade can work safely and reliably is crucial to the operation of the engine. Various performance indexes of the blades become important indexes for measuring the development degree of the engine, particularly the capability of the turbine blades for bearing high temperature. In summary, the development level of the turbine blade is an important mark for measuring the development level of the gas turbine in one country.
Currently, the turbine blade front temperature of a gas turbine has already exceeded the withstand temperature of its material. The blade can be guaranteed to work safely and reliably, and the blade is mainly achieved through two ways, namely the high-temperature resistance of the material is improved, and the temperature of the blade is reduced through a cooling mode with stronger cooling capacity. From the existing data, the temperature before the turbine is increased by 22K year on average in the past decades, wherein 70 percent of the temperature is due to the adoption of a more effective cooling mode, and 30 percent of the temperature is due to the improvement of the heat resistance of the component material and the development of the production process. With the development of cooling mode and the introduction of new heat transfer and heat exchange mechanism, the temperature before the turbine will gradually increase.
Advanced gas turbine designs have increased efficiency by increasing the initial temperature of the gas, and in the past, the initial temperature of the gas has been increased by developing high temperature resistant materials and cooling techniques to ensure that the turbine material can meet strength requirements and service life under high temperature gas. The more the cooling air is used, the more the power consumption of the air compressor is, so that the resistance loss of the cooling air is reduced, the work of the air compressor is reduced, and the efficiency of the gas turbine is improved. Nowadays, not only the efficiency is improved, but also the pollution of the gas to the environment is reduced, so that the air generated by the compressor needs to enter a combustion chamber more to participate in combustion, and the emission of pollutants is reduced. Therefore, the air used for cooling will be reduced. The reduction in air volume presents challenges to the design of the cooling structure of the turbine.
The cooling methods mainly adopted today are impingement cooling, convection cooling, film cooling, and transpiration cooling. The film cooling is an external cooling mode that cooling gas of an internal cooling channel forms a layer of film with lower temperature outside the turbine blade through a film hole connected with the cooling gas so as to isolate high-temperature gas. Film cooling is distributed at various locations on the blade and therefore plays an important role.
Disclosure of Invention
The invention aims to provide a turbine blade mixed cooling structure combining micro staggered ribs and air film holes, which further improves the cooling effect and the high temperature resistance of a blade.
The purpose of the invention is realized as follows:
the invention relates to a turbine blade mixed cooling structure combining a micro staggered rib and a film hole, which is characterized in that: including the blade body, the side is pressure surface, suction surface respectively around the blade body, and the blade body blade root is the cooling gas entry, sets up cooling convergent passageway in the blade body and sets up serpentine channel through the baffle, is separated by through the inner wall between cooling convergent passageway and the serpentine channel, sets up the post rib in the cooling convergent passageway, sets up crisscross rib cooling channel in the serpentine channel, sets up crisscross rib in the crisscross rib cooling channel.
The present invention may further comprise:
1. the staggered ribs are of a 3D kagome structure.
2. The inside of the staggered rib is provided with a micro air film hole which leads to the outside of the blade body, and air flowing to the outside of the blade body through the micro air film hole forms an air film on the outside of the blade body.
The invention has the advantages that:
1. the micro-channels increase the internal heat exchange area.
2. The staggered ribs are cooling structures with high heat exchange performance.
3. The staggered ribs have micro-holes therein forming film cooling channels.
4. This structure reduces thermal stress.
Drawings
FIG. 1a is a cross-sectional view of the present invention, and FIG. 1b is a cross-sectional view A;
FIG. 2 is a schematic view of a hybrid structure of staggered rib air film holes;
FIG. 3 is a cross-ribbed inlet hole on the inner wall of the blade;
FIG. 4 is a three-dimensional schematic view of a staggered rib channel;
FIG. 5 is a schematic view of cooling air flow through the interleaved rib channels and film holes.
Detailed Description
The invention will now be described in more detail by way of example with reference to the accompanying drawings in which:
referring to fig. 1-5, the hybrid cooling structure of turbine blade with micro staggered rib structure and air film combined according to the present invention mainly includes a general turbine blade internal serpentine channel cooling structure, staggered ribs with micro air film holes, and cooling channels with staggered ribs. The internal serpentine channel cooling structure of the turbine blade can improve the heat exchange performance of the blade. The cooling gas enters the cooling channel with the staggered ribs close to the outer part from the serpentine channel through the transmission channel, and part of the gas flows to the outer part of the blade through the micro gas film holes in the staggered ribs to form a gas film.
The cooling air passes through the cooling channels from the root into the interior of the blade, part of the cooling air passing through the cooling tapering channels with the stud ribs 3 in the region of the trailing edge. The remaining gas enters the cooling channels with alternating ribs and serpentine channels. After the gas enters, the two cooling channels are separated by the inner wall, the gas flow is divided into two parts, the suction surface 1 and the pressure surface 2 of the blade are respectively cooled, and the two parts are the outer walls. As shown in fig. 4, the interlaced ribs are in a 3D kagome configuration, and cooling gas flows through the cooling channels to enhance wall heat exchange. As shown in fig. 5, after the cooling air of the staggered rib cooling channel flows through the staggered ribs, the outer wall surface of the blade is subjected to convective heat exchange cooling and then flows into the serpentine cooling channel; the cooling air of the serpentine channel enters the inside of the staggered ribs through the open hole pattern 3 of the inner wall, and then flows out through the film holes of the outer wall surface of the blade to form a cooling film outside the blade.
The invention relates to a turbine blade mixed cooling structure combining micro staggered ribs and film holes. The staggered ribs are provided with smaller pores which are communicated with the blade air film holes. The ribs in the staggered rib cooling channel are in a 3D kagome structure. The staggered rib channel is separated from the serpentine channel by an inner wall, the inner wall is provided with a vent hole, and the vent hole is communicated with an external vent hole.

Claims (2)

1. A turbine blade mixed cooling structure combining micro staggered ribs and air film holes is characterized in that: the cooling tapered passage is separated from the serpentine passage through an inner wall, a column rib is arranged in the cooling tapered passage, a staggered rib cooling passage is arranged in the serpentine passage, and staggered ribs are arranged in the staggered rib cooling passage;
the inside of the staggered rib is provided with a micro air film hole which leads to the outside of the blade body, and air flowing to the outside of the blade body through the micro air film hole forms an air film on the outside of the blade body.
2. The hybrid cooling structure of a turbine blade with micro staggered ribs and film holes as claimed in claim 1, wherein: the staggered ribs are of a 3D kagome structure.
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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Publication number Priority date Publication date Assignee Title
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
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
CN113107610B (en) * 2021-04-13 2023-05-26 西北工业大学 Through-slit type half-split-slit trailing edge cooling structure and turbine blade
CN113107608B (en) * 2021-04-13 2023-05-23 西北工业大学 Turbulent flow threaded hole cooling structure for turbine blade trailing edge and turbine blade
CN113236370B (en) * 2021-05-25 2023-04-25 杭州汽轮动力集团有限公司 Cooling structure of high-pressure moving blade of gas turbine
CN113669756B (en) * 2021-08-31 2022-05-10 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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JPH0223201A (en) * 1988-07-13 1990-01-25 Toshiba Corp Turbine blade
US7713027B2 (en) * 2006-08-28 2010-05-11 United Technologies Corporation Turbine blade with split impingement rib
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

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