CN108412555B - The cavity jet stream of array improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat - Google Patents
The cavity jet stream of array improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat Download PDFInfo
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- CN108412555B CN108412555B CN201810215273.6A CN201810215273A CN108412555B CN 108412555 B CN108412555 B CN 108412555B CN 201810215273 A CN201810215273 A CN 201810215273A CN 108412555 B CN108412555 B CN 108412555B
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- cavity
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- prismatic
- jet pipe
- leaf
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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
- F01D5/147—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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
-
- 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
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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 present invention provides a kind of cavity jet streams of array to improve the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat, including blade body, several cavity fluidic architectures are equipped with to trailing edge in the leading edge of the Ye Dingcong blade body of blade body, each cavity fluidic architecture includes prismatic cavity and jet pipe, the bottom surface of prismatic cavity is arranged in the jet pipe, prismatic cavity outside jet pipe connection and the cooled gas path inside blade body, angle is equipped between jet pipe and corresponding prismatic cavity bottom surface, the maximum height of the prismatic cavity and the ratio of blade body height are 0.5%-4%.The present invention can further suppress clearance leakage of blade tip flowing, weaken the leakage vortices breakdown of leaf grating suction surface side, reduce the energy loss as caused by clearance leakage of blade tip compared to the leaf top of the turbine rotor blade grid with curved cavity；This self cooled cavity fluidic architecture can also be effectively improved the heat transfer characteristic of cavity side walls and leaf top surface.
Description
Technical field
The invention belongs to turbine blade field, improves blade-tip leakage flow more particularly, to a kind of cavity jet stream of array
Dynamic and heat exchange turbine moving blade.
Background technique
The high property of aero-engine depends on the fuel gas temperature for improving turbine inlet, is but degrading turbine first-stage and leads/move
The thermal environment of blade.Blade tip clearance between turbine moving blade and casing provides needed for blade centrifugal movement and expanded by heating
Radial nargin, effective guarantee intimate friction free relative motion between turbine moving blade and casing.High temperature fluid in channel
On leaf top, transverse-pressure gradient accelerates into gap under driving, after separation, the again processes such as attached occur in gap, from suction surface one
It flows out and participates in forming leakage whirlpool in side.Leakage flow increases the combustion gas energy loss for flowing through turbine moving blade, is to cause turbine
The important sources of movable vane aerodynamic loss.And it accelerates into high temperature fluid in the channel in gap and is further degrading changing near leaf top
Heat condition increases the thermic load in the region Ye Ding.Therefore, how to reduce clearance leakage of blade tip flow and leaf top thermic load has become
The critical evaluation index of turbine rotor blade leaf top moulding.
For no shroud turbine moving blade, the main control means of clearance leakage of blade tip flow and leaf top thermic load are reduced
Have: leaf top geometric modeling, labyrinth seal, leaf top jet stream etc..Leaf top geometric modeling and labyrinth seal are weakened without shroud movable vane
The important method of clearance leakage of blade tip.Wherein, the moulding of groove leaf top is similar to the effect of labyrinth seal, has been widely used
And research.The structure can reduce the thermic load of gap leakage flow rate and the region Ye Ding, improve turbine efficiency.It is controlled using leaf top jet stream
The research of clearance leakage of blade tip flowing processed is to arrange Gas Cooling pipe in turbine rotor blade leaf top surface, in the tool that leaf top surface applies
There is the jet stream contrary with leakage flow to be able to suppress clearance leakage of blade tip flowing.And leaf top jet stream and groove leaf roof construction
Main passive combination control technology had both reduced clearance leakage flow and energy loss, it helps improves the heat-exchange performance in the region Ye Ding
Energy.But above-mentioned control technology is it is difficult to ensure that the leakage flow control on balanced leaf top and heat exchange property improve, about high performance turbine
The leaf top moulding of movable vane needs further research.
Our seminars turbine rotor blade grid leaf top arrange prism cavity and combined type curved cavity studies have shown that by this
Kind, which is applied, can reduce turbine leaf top clearance leakage flow in the near-hermetic structure on turbine moving blade leaf top, and reduction flows through turbine
The gas energy of leaf grating is lost.Under the severe high heat load environment on true turbine leaf top, the sidewall surfaces of this curved cavity
Directly by the impact of leak fluid, the heat exchange environment of reinforcing makes the easily ablated damage of cavity side walls, has seriously affected this
Application value of the kind turbine rotor blade grid leaf top moulding in true high performance turbine movable vane piece.It is a kind of both right therefore, it is necessary to develop
Leaf top surface and cavity side walls are effectively cooling, and do not damage the active Flow Control technology that cavity inhibits leakage flow.
Summary of the invention
In view of this, the cavity jet stream that the invention is directed to a kind of array improves what blade-tip leakage flow moved and exchanged heat
Turbine moving blade can further suppress clearance leakage of blade tip flowing and reduce the gas energy loss for flowing through leaf grating, and pass through
Cooling blast realizes effectively from cooling effect cavity internal structure.
In order to achieve the above objectives, the technical solution of the invention is achieved in that
A kind of turbine moving blade that the cavity jet stream improvement blade-tip leakage flow of array is moved and exchanged heat, including blade body,
The leading edge of the Ye Dingcong blade body of the blade body is equipped with several cavity fluidic architectures to trailing edge, and each described is recessed
Chamber fluidic architecture includes prismatic cavity and jet pipe, and the bottom surface of prismatic cavity is arranged in the jet pipe, described
Prismatic cavity outside jet pipe connection and the cooled gas path inside blade body, the jet pipe and corresponding rib
Angle α c is equipped between column type cavity bottom surface, the maximum height d and the ratio of blade body height H of the prismatic cavity are
0.5%-4%.
Further, the prismatic cavity is regular prism-shaped cavity or slant edge column type cavity.
Further, the arranged direction of the prismatic cavity is the side or angle face blade geometry flow inlet angle side of prism
To, leaf grating pressure face molded line direction or leaf grating suction surface molded line direction.
Further, blade tip clearance height is h, and the bottom surface side length L of prismatic cavity is 1.25-2.5h, prismatic cavity
Height d be not more than 4.0h, the caliber Dc of jet pipe is not more than 0.5h.
Further, the angle α c is within the scope of 30 ° -90 °.
Further, the prismatic cavity is regular hexagonal prism cavity, and the bottom surface side length L of the regular hexagonal prism cavity is
2h, the regular hexagonal prism cavity height d are h, and the caliber Dc of the jet pipe is 0.5h, the axis of the jet pipe with
Angle α c between regular hexagonal prism cavity bottom surface is 30 °.
Compared with the existing technology, the cavity jet stream of array described in the invention improves what blade-tip leakage flow moved and exchanged heat
Turbine moving blade has the advantage that
The cavity jet stream of array of the present invention improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat, Jetstream fluid
It may participate in and strengthen the vorticla motion in the cavity of leaf top, so that intracavitary vortex makees the obstruction for flowing through the leak fluid above cavity
With enhancing.Compared to the leaf top of the turbine rotor blade grid with curved cavity, clearance leakage of blade tip flow further declines, to press down
The initial stage formation and development in the leakage whirlpool of leaf grating suction surface processed side, changes the space cloth of secondary flow structure in leaf grating upper channel
Office.Meanwhile weakening the leakage vortices breakdown of leaf grating suction surface side, reduce the energy loss as caused by clearance leakage of blade tip.Cavity
Fluidic architecture can be effectively for severe heat transfer boundary condition local in cavity side walls, by Jetstream fluid and bottom leak fluid in chamber
Abundant blending under interior swirling action reduces the gas temperature for being covered on cavity side walls and leaf top surface, this self cooled recessed
Chamber fluidic architecture can effectively improve the heat transfer characteristic of cavity side walls and leaf top surface.
The cavity jet stream of array of the present invention improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat, by Ye Dingshi
Lobus cardiacus piece becomes the blade with several cavitys, and the abradability on leaf top can be enhanced, realize smaller gap permissible value.Separately
Outside, cavity leaf top can also reduce the weight on turbine moving blade leaf top.
Detailed description of the invention
The attached drawing for constituting a part of the invention is used to provide to further understand the invention, present invention wound
The illustrative embodiments and their description made are used to explain the present invention creation, do not constitute the improper restriction to the invention.?
In attached drawing:
Turbine cascade meridian view Fig. 1 of the invention；
Fig. 2 is the geometric representation of cavity fluidic architecture；
Fig. 3 is the geometrically symmetric sectional view of cavity fluidic architecture；
Fig. 4 is the turbine rotor blade grid schematic diagram for arranging cavity fluidic architecture；
Fig. 5 A is the static pressure coefficient distribution map of the leaf grating casing with flat-top turbine rotor blade grid；
Fig. 5 B is the static pressure coefficient distribution map for arranging the leaf grating casing of turbine rotor blade grid of curved cavity；
Fig. 5 C is the static pressure coefficient distribution map for arranging the leaf grating casing of turbine rotor blade grid of cavity fluidic architecture；
Fig. 6 A is that the leaf grating of flat-top turbine rotor blade grid exports total pressure loss coefficient distribution map；
Fig. 6 B is the leaf grating outlet total pressure loss coefficient distribution map for arranging the turbine rotor blade grid of curved cavity；
Fig. 6 C is the leaf grating outlet total pressure loss coefficient distribution map for arranging the turbine rotor blade grid of curved cavity；
Fig. 7 compared leakage flow, the rate of discharge average total pressure of three kinds of turbine rotor blade grid with different leaf roof constructions
It loses, the coefficient of heat transfer histogram of leaf top surface and cavity side walls.
Description of symbols:
1- casing, 2- wheel hub, 3- blade body, 4- cavity fluidic architecture, 5- costa, 6- trailing edge line, 101- prismatic
Cavity, 102- jet pipe, 103- leaf top.
Specific embodiment
It should be noted that in the absence of conflict, the feature in embodiment and embodiment in the invention can
To be combined with each other.
The present invention will be described in detail below with reference to the accompanying drawings and embodiments creates.
As Figure 1-Figure 2, the present invention applies in turbine moving blade, blade body 3 install on the hub 2, casing 1 with
Leaf grating runner is formed between wheel hub 2,5,6 respectively indicate the costa of blade body 3 and trailing edge line, on the leaf top of blade body 3
103 are equipped with several cavity fluidic architectures 4 from the leading edge of blade body 3 to trailing edge, and each cavity fluidic architecture 4 wraps
Prismatic cavity 101 and jet pipe 102 are included, the bottom surface of prismatic cavity 101 is arranged in the jet pipe 102, and described penetrates
Flow tube 102 is connected to the cooled gas path inside external prismatic cavity 101 and blade body 3, the jet pipe 102 and
Angle α c, the maximum height d and blade body 3 of the prismatic cavity 101 are equipped between corresponding 101 bottom surface of prismatic cavity
The ratio of height H is 0.5%-4%.
Blade tip clearance height is h, and the bottom surface side length L of prismatic cavity 101 is 1.25-2.5h, the height of prismatic cavity 101
It spends d and is not more than 4.0h, the caliber Dc of jet pipe 102 is not more than 0.5h.
The different positions of cavity bottom can be arranged in the outlet port of jet pipe 102 according to inner space leakage flow situation
It sets, the jet pipe 102 in Fig. 2 is disposed in 101 bottom center of prismatic cavity.
As shown in figure 3, the angle α c between 101 bottom surface of axis and prismatic cavity of jet pipe 102 can be according in gap
Portion's leakage flow situation is configured, and generally 30 ° -90 °.
As shown in figure 4, being specific arrangement form of the cavity fluidic architecture 4 on leaf top 103, i.e. prismatic cavity 102
Arranged direction is the side or angle face blade geometry air inlet angular direction of prism, and prismatic cavity is regular hexagonal prism cavity, positive six rib
The bottom surface side length L of column cavity is 2h, and cavity height d is h, and the caliber Dc of jet pipe 102 is 0.5h, the axis of jet pipe 102 with
Angle α c between regular hexagonal prism cavity bottom surface is 30 °；Needed between adjacent cavity according to material process intensity there are certain
Wall thickness, and delete during shift copy across or extremely close to blade pressure/suction surface jet stream cavity unit, thus obtain
Cavity jet stream after arrangement is independent, complete.
The arranged direction of prismatic cavity 102 may be side or angle face leaf grating pressure face molded line direction or the leaf of prism
Grid suction surface molded line direction.
In order to verify effect of the invention, to flat-top, arrange curved cavity and arrange cavity fluidic architecture
Turbine rotor blade grid carried out numerically modeling.The direction of jet pipe is consistent in this time verifying work, is directed to close to pressure face one
The cavity side walls of side.Physical simulation parameter and result are as follows:
Turbine rotor blade grid and cavity fluidic architecture parametric geometry parameter for simulating is as shown in the table:
| Axial chord length Cax (mm) | 100 |
| Chord length b/Cax | 1.3 |
| Leaf grating height H/Cax | 1.6 |
| Clearance height h/H | 0.01 |
| Leaf grating geometry flow inlet angle α k (°) | -40.70 |
| Leaf grating geometry efflux angles β k (°) | 67.40 |
| Leaf grating established angle γ (°) | 40.20 |
| The angle of attack (°) | 0 |
| Cavity bottom surface side length L/h | 2 |
| Cavity height d/h | 1 |
Cascade blade is stretched to obtain by the leaf top-type line of 1.5 grades of turbine rotor blades of LISA, and inflow Mach number 0.09 is based on
The Reynolds number of inlet velocity and blade axial direction chord length is 1.92 × 105.Numerical value calculates the turbulence model used as two equation of k- ω
Model, the inlet boundary of computational domain are located at the axial chord positions of 1.5 times of leading edge upstream, give incoming flow stagnation pressure, total temperature；Export side
Boundary is located at the axial chord positions in 2.5 times of trailing edge downstream, given pressure.Wall surface uses isothermal non-slip condition.
Fig. 5 A, Fig. 5 B, Fig. 5 C compared leaf top with flat-tope structure, curved cavity and three kinds of cavity fluidic architecture different knots
The casing static pressure coefficient distribution situation of the turbine rotor blade grid of structure, it can be found that with flat-top and the turbine of curved cavity is arranged
Moving blades are compared, and after cavity fluidic architecture, low-pressure area of the inner space of turbine rotor blade grid close to pressure face side disappears.
Static pressure distribution inside blade tip clearance can effectively hinder channel interior fluid to enter blade tip clearance.
Fig. 6 A, Fig. 6 B, Fig. 6 C compared leaf top with flat-tope structure, curved cavity and three kinds of cavity fluidic architecture different knots
Section total pressure loss coefficient distribution situation at the axial chord positions in 0.3 times of the turbine rotor blade grid trailing edge downstream of structure, Ke Yifa
Now with flat-top and compared with arranging the turbine rotor blade grid of curved cavity, after cavity fluidic architecture, the outlet
Pitot loss changes in distribution is obvious, is mainly reflected in the corresponding loss region area in leakage whirlpool and intensity declines, and upper channel whirlpool
The area in corresponding loss region is increased slightly.
As shown in fig. 7, it is average total to compared the leakage flow with the turbine rotor blade grid of different leaf roof constructions, rate of discharge
Crushing loses, the coefficient of heat transfer of leaf top surface and cavity side walls.It can be found that being arranged recessed compared with the turbine cascade with flat-top
The leakage flow and pitot loss of the turbine rotor blade grid of cavity configuration decline, but the heat exchange enhancing of leaf top surface；Using arranging
The leakage flow and pitot loss of the turbine rotor blade grid of cavity fluidic architecture further decline, leaf top surface and cavity side walls face
Heat exchange situation is improved.
As it can be seen that the present invention reduces turbine in the design scheme of turbine rotor blade grid leaf top surface arrangement cavity fluidic architecture
The clearance leakage of blade tip flow and outlet pitot loss, cavity jet stream of moving blades can be realized to the self cooling of cavity inner space
But, the heat exchange situation in leaf top surface and cavity side walls face is improved.
The foregoing is merely the preferred embodiments of the invention, are not intended to limit the invention creation, all at this
Within the spirit and principle of innovation and creation, any modification, equivalent replacement, improvement and so on should be included in the invention
Protection scope within.
Claims (2)
1. a kind of cavity jet stream of array improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat, it is characterised in that: including leaf
Piece ontology (3), it is recessed equipped with several from the leading edge of blade body (3) to trailing edge on the leaf top (104) of the blade body (3)
Chamber fluidic architecture (4), each cavity fluidic architecture (4) include prismatic cavity (101) and jet pipe (102), institute
Prismatic of jet pipe (102) setting stated outside the bottom surface of prismatic cavity (101), the jet pipe (102) connection
The internal cooled gas path of cavity (101) and blade body (3), the jet pipe (102) and corresponding prismatic cavity
(101) angle α c, the ratio of the maximum height d and blade body (3) height H of the prismatic cavity (101) are equipped between bottom surface
Value is 0.5%-4%；The direction of jet pipe is consistent, is directed to the cavity side walls close to pressure face side；Jet pipe (102) is by cloth
It sets in prismatic cavity (101) bottom center；The prismatic cavity (101) is regular prism-shaped cavity or slant edge column type cavity；
The arranged direction of prismatic cavity (101) is the side or angle face blade geometry air inlet angular direction, leaf grating pressure face molded line of prism
Direction or leaf grating suction surface molded line direction；Blade tip clearance height is h, and the bottom surface side length L of prismatic cavity (101) is 1.25-
2.5h, the height d of prismatic cavity (101) are not more than 4.0h, and the caliber Dc of jet pipe (102) is not more than 0.5h；The angle α
C is within the scope of 30 ° -90 °.
2. the cavity jet stream of array according to claim 1 improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat,
Be characterized in that: the prismatic cavity (101) is regular hexagonal prism cavity, and the bottom surface side length L of the regular hexagonal prism cavity is 2h, institute
The regular hexagonal prism cavity height d stated is h, and the caliber Dc of the jet pipe (102) is 0.5h, the jet pipe (102)
Angle α c between axis and regular hexagonal prism cavity bottom surface is 30 °.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201810215273.6A CN108412555B (en) | 2018-03-15 | 2018-03-15 | The cavity jet stream of array improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat |
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| CN201810215273.6A CN108412555B (en) | 2018-03-15 | 2018-03-15 | The cavity jet stream of array improves the turbine moving blade that blade-tip leakage flow is dynamic and exchanges heat |
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| CN112576316B (en) * | 2020-11-16 | 2023-02-21 | 哈尔滨工业大学 | Turbine blade |
| CN112594011B (en) * | 2020-12-15 | 2022-09-13 | 中国科学院工程热物理研究所 | Active flow separation regulation and control device in high-load low-pressure turbine |
| CN113758968B (en) * | 2021-09-30 | 2022-08-05 | 西安交通大学 | Experimental system and steady-state experimental method for measuring turbine movable blade top heat exchange coefficient |
Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1267041A2 (en) * | 2001-06-11 | 2002-12-18 | ALSTOM (Switzerland) Ltd | Cooled turbine blade |
| CN103422912A (en) * | 2013-08-29 | 2013-12-04 | 哈尔滨工程大学 | Turbine with moving blades with pits at blade tops |
| CN205618204U (en) * | 2016-05-19 | 2016-10-05 | 中航商用航空发动机有限责任公司 | Blade apex impingement cooling structure and aeroengine turbine rotor |
Family Cites Families (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107246285A (en) * | 2017-05-19 | 2017-10-13 | 燕山大学 | A kind of turbomachine clearance leakage of blade tip is combined passive control methods |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1267041A2 (en) * | 2001-06-11 | 2002-12-18 | ALSTOM (Switzerland) Ltd | Cooled turbine blade |
| CN103422912A (en) * | 2013-08-29 | 2013-12-04 | 哈尔滨工程大学 | Turbine with moving blades with pits at blade tops |
| CN205618204U (en) * | 2016-05-19 | 2016-10-05 | 中航商用航空发动机有限责任公司 | Blade apex impingement cooling structure and aeroengine turbine rotor |
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