CN108757047A - Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column - Google Patents
Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column Download PDFInfo
- Publication number
- CN108757047A CN108757047A CN201810515164.6A CN201810515164A CN108757047A CN 108757047 A CN108757047 A CN 108757047A CN 201810515164 A CN201810515164 A CN 201810515164A CN 108757047 A CN108757047 A CN 108757047A
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- China
- Prior art keywords
- column
- droplet
- shaped rib
- blade
- gas turbine
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- 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.)
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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
Abstract
The present invention is to provide a kind of turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column.Turbo blade including being internally provided with cooling duct further includes the droplet-shaped rib of column, and the droplet-shaped rib of column is located at the trailing edge region of turbo blade, and droplet-shaped rib of column both ends are fixedly linked with the suction surface of turbo blade with pressure face respectively.The present invention uses the droplet-shaped rib of column, the opposite cylindrical type rib of column, integrated heat efficiency that can improve 20%, therefore has many advantages, such as more effectively to inhibit the increase of drag losses, improves heat exchange property.The present invention can be used for turbine rotor blade, can be used for turborotor.
Description
Technical field
The present invention relates to a kind of turbine blade of gas turbine.
Background technology
Gas turbine has that light weight, small, single-machine capacity are big, start 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 property indices of blade become the important finger of measured engine development degree
Mark, especially turbo blade can bear the ability of high temperature.In short, the development level of turbo blade, which becomes, weighs 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.Ensure that blade can be safe
It reliably works, is mainly realized by two approach, first, 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 carries every year on average
Rise 22K, wherein 70% is because using the mode of being more efficiently cooled, and 30% is because component materials heat resistance carries
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 be gradual
It improves.
Advanced gas turbine design is to improve 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, combustion engine efficiency is improved.Nowadays, efficiency is not only improved, also to reduce pollution of the combustion gas to environment, therefore
Air is generated from compressor, needs more to enter combustion chamber participation 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.Therefore, nowadays combustion engine turbine leaf
The purpose of design of piece cooling structure, main there are two aspects, first, improving heat exchange property, reduce leaf temperature；Second is that reducing stream
Dynamic loss reduces cooling air consumption.
Convection current cooling is cooled down to blade interior in a manner of heat convection.Turbulence columns strengthen convection current cooling usually with multiple rows of
The form of structure applies the trailing edge in blade.Trailing edge channel is generally relatively narrow, destruction of the turbulence columns to boundary layer, and fluid turbulent degree increases
By force, heat exchange enhancing.
Invention content
The purpose of the present invention is to provide a kind of heat exchange properties that can improve turbine blade of gas turbine, reduce pressure damage
It loses, improves the turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column of integrated heat efficiency.
The object of the present invention is achieved like this：Turbo blade including being internally provided with cooling duct, further includes water droplet
The type rib of column, the droplet-shaped rib of column are located at the trailing edge region of turbo blade, droplet-shaped rib of column both ends respectively with the suction of turbo blade
Power face is fixedly linked with pressure face.
The present invention can also include：
1, the droplet-shaped rib of column is interspersed between suction surface and pressure face.
2, the length of the droplet-shaped rib of column is gradually shortened with the tapered i.e. height change of cooling duct in blade trailing edge channel.
3, the droplet-shaped rib of column is divided into front and back two parts, and preceding partial cross section is semicircle, and rear partial cross section is tangent with semicircle
Two camber lines, two camber lines meet at a bit backward.
4, the suction surface of droplet-shaped rib of column both ends and turbo blade is fixedly linked with pressure face by way of model casting.
The present invention relates to cooling structures inside a kind of droplet-shaped rib of column for turbine blade of gas turbine, specifically
It is a kind of a kind of structure for raising heat exchange improving turbine blade of gas turbine.
In order to improve the heat exchange property of turbine blade of gas turbine, the pressure loss is reduced, integrated heat efficiency is improved.The present invention
The inside cooling structure of turbine blade of gas turbine include internal cooling channel and the droplet-shaped rib of column, the droplet-shaped rib of column is main
Positioned at the trailing edge region of turbo blade, rib of column both ends are fixedly linked with the suction surface of blade and pressure face and are in the cloth that interlocks respectively
It sets.Blade trailing edge channel is tapered, and the length of the rib of column shortens with the height change in channel.The droplet-shaped rib of column is divided into front and back two
Point, leading portion section is the semicircle of certain diameter (D), and back segment section is two camber lines tangent with semicircle, and two camber lines are backward
It meets at a bit, the length in the semicircle center of circle to intersection point is P, and global shape is in droplet-shaped.
Compared with prior art, advantages of the present invention has：
First, the droplet-shaped rib of column has the function of destroying flow boundary layer, improves wall surface heat transfer property, improves heat-transfer surface
Product, therefore improve cooling performance.The droplet-shaped rib of column 3 prolongs shortening for flow direction rib of column length, not only without weakening heat exchange effect
Fruit, and shorten the length of cooling duct 4；Since trailing edge region blade is relatively thin, the sectional area of the droplet-shaped rib of column 3 increases
Its structural strength can be improved.Streamwise, 3 leading portion of the droplet-shaped rib of column has the effect of generating separating layer, and the second half section has
Play the role of inhibiting the generation in energy loss whirlpool, the pressure loss can be greatly reduced while improving heat exchange.Opposite cylindrical type
The rib of column, integrated heat efficiency improves 20%, therefore with the increase for more effectively inhibiting drag losses, it is excellent to improve heat exchange property etc.
Point.
The present invention can be used for turbine rotor blade, can be used for turborotor.
Description of the drawings
Fig. 1 is the schematic structural cross-sectional view of the present invention；
Fig. 2 is the A-A sectional views of Fig. 1.
Fig. 3 is the droplet-shaped rib of column schematic cross-section of the present invention.
Specific implementation mode
It illustrates below and the present invention is described in more detail.
Turbine blade of gas turbine of the invention is the turbo blade for being internally provided with cooling duct combined with Figure 1 and Figure 2,
The trailing edge region of turbo blade is provided with the droplet-shaped rib of column 3, the both ends of the every droplet-shaped rib of column respectively with the suction of turbo blade
Power face 1 is fixedly linked with pressure face 2 by way of model casting.
Turbo blade blade root tenon is connected with the turbine disk, and middle part of blade is serpentine cooling channel, carries fin, and raising is changed
Heat；Front end is impinging cooling structure, and air-flow enters impact chamber by impact opening；Trailing edge region is rib of column cooling structure.Cooling air
Stream is entered by blade root, and cooling gas flows into bucket front, middle part, trailing edge region.Air-flow is carried out cold by blade trailing edge region 4
But, it is flowed out by trailing edge slit.The droplet-shaped rib of column is in be staggered, and shorten along the length of the airflow direction rib of column.The rib of column
Arrangement mode, wrong row's mode are better than in-line arrangement mode.
In conjunction with Fig. 3, the droplet-shaped rib of column is divided into front and back two parts, and leading portion section is the semicircle of certain diameter D, back segment section
It is two camber lines tangent with semicircle, two camber lines are met at a bit backward, and the length in the semicircle center of circle to intersection point is P, global shape
In droplet-shaped.
The present invention main feature can also include：
1, in the cooling channel, with the height change of cooling duct, the variation of rib of column length.The length and cooling gas of the rib of column
Flow velocity, tapered channels height is related, and there are a best relations.
2, cooling duct is tapered along airflow direction, and the height of the rib of column shortens, and ratio of height to diameter reduces.
3, the height of cooling duct reduces, and the length of the rib of column reduces therewith.
4, rib of column structural support area is big, and the intensity of structure is high.
5, the arrangement mode of the rib of column can be alternating expression, can also be in-line arrangement formula.
Claims (9)
1. a kind of turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column, including it is internally provided with cooling duct
Turbo blade, it is characterized in that：Further include the droplet-shaped rib of column, the droplet-shaped rib of column is located at the trailing edge region of turbo blade, water
Drop type rib of column both ends are fixedly linked with the suction surface of turbo blade with pressure face respectively.
2. the turbine blade of gas turbine according to claim 1 with cooling structure inside the droplet-shaped rib of column, feature
It is：The droplet-shaped rib of column is interspersed between suction surface and pressure face.
3. the turbine blade of gas turbine according to claim 1 or 2 with cooling structure inside the droplet-shaped rib of column, special
Sign is：The length of the droplet-shaped rib of column is gradually shortened with the tapered i.e. height change of cooling duct in blade trailing edge channel.
4. the turbine blade of gas turbine according to claim 1 or 2 with cooling structure inside the droplet-shaped rib of column, special
Sign is：The droplet-shaped rib of column is divided into front and back two parts, and preceding partial cross section is semicircle, and rear partial cross section is tangent with semicircle two
Camber line, two camber lines are met at a bit backward.
5. the turbine blade of gas turbine according to claim 3 with cooling structure inside the droplet-shaped rib of column, feature
It is：The droplet-shaped rib of column is divided into front and back two parts, and preceding partial cross section is semicircle, and rear partial cross section is two arcs tangent with semicircle
Line, two camber lines are met at a bit backward.
6. the turbine blade of gas turbine according to claim 1 or 2 with cooling structure inside the droplet-shaped rib of column, special
Sign is：The suction surface of droplet-shaped rib of column both ends and turbo blade is fixedly linked with pressure face by way of model casting.
7. the turbine blade of gas turbine according to claim 3 with cooling structure inside the droplet-shaped rib of column, feature
It is：The suction surface of droplet-shaped rib of column both ends and turbo blade is fixedly linked with pressure face by way of model casting.
8. the turbine blade of gas turbine according to claim 4 with cooling structure inside the droplet-shaped rib of column, feature
It is：The suction surface of droplet-shaped rib of column both ends and turbo blade is fixedly linked with pressure face by way of model casting.
9. the turbine blade of gas turbine according to claim 5 with cooling structure inside the droplet-shaped rib of column, feature
It is：The suction surface of droplet-shaped rib of column both ends and turbo blade is fixedly linked with pressure face by way of model casting.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810515164.6A CN108757047A (en) | 2018-05-25 | 2018-05-25 | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810515164.6A CN108757047A (en) | 2018-05-25 | 2018-05-25 | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column |
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| CN108757047A true CN108757047A (en) | 2018-11-06 |
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| CN201810515164.6A Pending CN108757047A (en) | 2018-05-25 | 2018-05-25 | Turbine blade of gas turbine with cooling structure inside the droplet-shaped rib of column |
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Cited By (5)
| 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 |
| CN110130996A (en) * | 2019-05-09 | 2019-08-16 | 西北工业大学 | A kind of grid seam cooling structure with fishtail turbulence columns |
| CN110714802A (en) * | 2019-11-28 | 2020-01-21 | 哈尔滨工程大学 | Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade |
| CN111350549A (en) * | 2019-12-30 | 2020-06-30 | 中国科学院工程热物理研究所 | Cooling structure suitable for be rich in and fire working medium turbine high temperature quiet leaf |
| CN114370305A (en) * | 2022-01-25 | 2022-04-19 | 杭州汽轮动力集团有限公司 | Gas turbine stationary blade composite cooling structure |
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| CA2828422A1 (en) * | 2012-09-25 | 2014-03-25 | Pratt & Whitney Canada Corp. | Internally cooled gas turbine engine airfoil |
| CN107013255A (en) * | 2017-06-01 | 2017-08-04 | 西北工业大学 | A kind of turbine blade tail flow-disturbing with continuous straight rib partly splits seam cooling structure |
| CN107060889A (en) * | 2017-04-19 | 2017-08-18 | 西北工业大学 | A kind of double disc turbine disks with disk chamber turbulence columns |
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| CN1851239A (en) * | 2005-04-22 | 2006-10-25 | 联合工艺公司 | Airfoil trailing edge cooling |
| CN101021166A (en) * | 2006-02-15 | 2007-08-22 | 联合工艺公司 | Turbine blade with radial cooling channels |
| CN101581235A (en) * | 2009-06-25 | 2009-11-18 | 上海交通大学 | Turbine blade compound cooling structure with sunken internal pin |
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| CN107060889A (en) * | 2017-04-19 | 2017-08-18 | 西北工业大学 | A kind of double disc turbine disks with disk chamber turbulence columns |
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Cited By (8)
| 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 |
| CN110130996A (en) * | 2019-05-09 | 2019-08-16 | 西北工业大学 | A kind of grid seam cooling structure with fishtail turbulence columns |
| CN110714802A (en) * | 2019-11-28 | 2020-01-21 | 哈尔滨工程大学 | Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade |
| CN110714802B (en) * | 2019-11-28 | 2022-01-11 | 哈尔滨工程大学 | Intermittent staggered rib structure suitable for internal cooling of high-temperature turbine blade |
| CN111350549A (en) * | 2019-12-30 | 2020-06-30 | 中国科学院工程热物理研究所 | Cooling structure suitable for be rich in and fire working medium turbine high temperature quiet leaf |
| CN111350549B (en) * | 2019-12-30 | 2022-07-26 | 中国科学院工程热物理研究所 | Cooling structure suitable for be rich in and fire working medium turbine high temperature quiet leaf |
| CN114370305A (en) * | 2022-01-25 | 2022-04-19 | 杭州汽轮动力集团有限公司 | Gas turbine stationary blade composite cooling structure |
| CN114370305B (en) * | 2022-01-25 | 2024-02-20 | 杭州汽轮控股有限公司 | Composite cooling structure for turbine stator blades of gas turbine |
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Application publication date: 20181106 |