CN107725115A - The aerofoil profile air film hole and electrode of aero-engine hot-end component - Google Patents
The aerofoil profile air film hole and electrode of aero-engine hot-end component Download PDFInfo
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- CN107725115A CN107725115A CN201710293032.9A CN201710293032A CN107725115A CN 107725115 A CN107725115 A CN 107725115A CN 201710293032 A CN201710293032 A CN 201710293032A CN 107725115 A CN107725115 A CN 107725115A
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- cold air
- aerofoil profile
- film hole
- hole
- air film
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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
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a kind of aerofoil profile air film hole of aero-engine hot-end component and electrode.The aerofoil profile air film hole of aero-engine hot-end component, including cold air inlet and cold air outlet, the centre hole axis of aerofoil profile air film hole are laid with the inclined angle α of hot-end component wall body, the Kong Zhanxiang width of aerofoil profile air film hole is gradually increased to cold air outlet direction from cold air inlet and hole thickness is gradually thinning, so as to be flowed on the hot-end component outer surface that the cold air flowed into from cold air inlet gradually extends to both sides and is attached to after slowing down ejection along gradually thinning cold air outlet outside cold air outlet.On the one hand so that cold air is easy to be attached on the wall of hot-end component after spraying from outlet, on the other hand make it that the speed of cold air into high-temperature fuel gas is smaller, reduces the pneumatic mixing loss of combustion gas and cold air, improve the pneumatic efficiency of turbo blade.Manufacture processing is simple, efficient.
Description
Technical field
The present invention relates to aero-engine hot-end component processing technique field, especially, is related to a kind of aero-engine heat
The aerofoil profile air film hole of end pieces.A kind of moreover, it relates to aerofoil profile air film for being used to process aero-engine hot-end component
The electrode in hole.
Background technology
In aero-engine, hot-end component is relied primarily on cold air heat convection to realize cooling, must be taken for this
Various enhanced heat exchanges or the measure heated to hot-end component of barrier hot combustion gas are to reach the mesh that cold air dosage is few, cold air effect is good
's.Advanced cooling scheme is to ensure hot-end component stabilization, the effective ways of reliability service, in actual applications basic cooling means
Mainly have:Convection current cooling, impinging cooling, diverging cooling and gaseous film control, wherein gaseous film control have been widely used in aviation
Compressor, combustion chamber in engine, especially on turbine, turn into one of Major Cooling Methods of numbers of hot-side engine parts.
Gaseous film control is to spray one cooling agent by the spout on wall to obstruct one kind that main combustion gas stream heats to wall
Thermal protection measure.Air film hole pass on current domestic exterior combustion chamber or turbo blade is broadly divided into three classes：
The first is cylindrical hole；
Second is cylindrical type development evolvement hole (droplet-shaped and dustpan shaped etc.)；
The third is two-dimentional groove profile, seam type hole.
Implementation is：From power traction of calming the anger take high pressure low temperature cold air by engine air system pipeline reach combustion chamber or
Turbo blade inner passage, cold air strengthen heat convection in passage and take away the partial heat of combustion chamber or turbo blade, together
When part cold air sprayed from the air film hole on combustion chamber or Turbine blade wall, this strand of cold air is in main flow and fluid Coanda effect
Downstream bent under effect, be adhered near wall, the relatively low cooling air film of temperature, the gas are formed between combustion gas stream and wall
Film influences of both being produced on the heat convection between combustion gas and wall, is on the one hand the influence in terms of cooling air film energy,
Due to cooling down the presence of air film, the heat convection driving temperature difference between combustion gas and wall is reduced, that is to say, that due to cooling down gas
Film temperature TcLess than the temperature T of main combustion gas streamg, thus the result of both collective effects (blending) is that combustion gas sidewind temperature declines,
Mixed gas recovery temperature (i.e. adiabatic wall temperature) T in combustion gas side being reduced in the presence of cooling air filmaw；On the other hand it is cooling air film momentum
The influence of aspect, due to the adherent injection of air film jet, add the disturbance of hot side air-flow.
Problems be present in existing gaseous film control：
The first cylindrical hole, processing technology is good, but cold air sprays into after high-temperature fuel gas the air film formed from air film hole
Area coverage it is small, effect of heat insulation is limited, and cylindrical type air film hole formed air film compare concentration so that cold air enters high temperature
The speed of combustion gas is big, causes the pneumatic mixing loss of combustion gas and cold air big, eventually reduces the pneumatic efficiency of turbo blade；
Second cylindrical type development evolvement hole (droplet-shaped and dustpan shaped etc.), compared with the good cooling results of cylindrical type air film hole,
The pneumatic mixing loss of combustion gas and cold air is larger, while processing technology is complicated, and processing efficiency is low；
The third two-dimentional groove profile, seam type hole, the cooling effectiveness of air film can be improved to a certain extent, but due to intensity
And the reason for process aspect and can not be applied in Practical Project.
The content of the invention
The invention provides a kind of aerofoil profile air film hole of aero-engine hot-end component and electrode, is sent out with solving existing aviation
The gaseous film control of motivation hot-end component, the area coverage of the air film formed after air film hole penetrating high-temperature fuel gas is small, effect of heat insulation
It is limited；The pneumatic mixing loss of combustion gas and cold air is big, and processing technology is complicated, the low technical problem of processing efficiency.
According to an aspect of the present invention, there is provided a kind of aerofoil profile air film hole of aero-engine hot-end component, including cold air
Entrance and cold air outlet, centre hole axis and the inclined angle α of hot-end component wall body of aerofoil profile air film hole are laid, aerofoil profile air film hole
Kong Zhanxiang width is gradually increased to cold air outlet direction from cold air inlet and hole thickness is gradually thinning, so as to be flowed into from cold air inlet
Cold air gradually extended to both sides and slow down along gradually thinning cold air outlet spray after be attached to hot junction portion outside cold air outlet
Part flows on outer surface.
Further, the slanted angle α of the hole axle of aerofoil profile air film hole is 20 °~70 °.
Further, the first ellipse that the pass of cold air inlet is laid using incline direction of the major axis along aerofoil profile air film hole
Perforate.
Further, the pass of cold air outlet uses second slotted eye of the both sides with rectangular side foramen alare, both sides rectangular side
Short-axis direction of the foramen alare along the second slotted eye is laid and laid along long axial symmetry；The second slotted eye and cold air of cold air outlet
The hole shape of first oval aperture of entrance, size and cloth set direction are identical.
Further, the second slotted eye is respectively arc-shaped transition between the rectangular side foramen alare of both sides.
Further, four angular vertexs of cold air outlet are respectively b1、b2、b3And b4, wherein b1With b4In same rectangular side
Foramen alare, rectangular opening side b1b4Midpoint be b5, b2With b3In same rectangular side foramen alare, rectangular opening side b2b3Midpoint be b7, b1With
b2And b3With b4Corresponding 2 points laid respectively on the second elliptical aperture short-axis direction；b1With b2Between there is the song arranged successively
Line point b9、b10、b6、b11And b12, b1b9With b12b2The respectively rectilinear end hole wall of rectangular side foramen alare, b9b10With b11b12Respectively square
Shape flank hole and the transition segmental arc of the second slotted eye, b6Major axis end points for the second slotted eye and be ellipse arc section
b10b11Arc midpoint；b3With b4Between there is the curve point b that arranges successively13、b14、b8、b15And b16, b3b13With b16b4Respectively
For the rectilinear end hole wall of rectangular side foramen alare, b13b14With b15b16The respectively transition arc of rectangular side foramen alare and the second slotted eye
Section, b8Major axis end points for the second slotted eye and be ellipse arc section b14b15Arc midpoint.
Further, b1、b2、b3And b4Corresponding entrance summit tie point in the first oval aperture is respectively a1、a2、
a3And a4, ellipse arc section a1a4Arc midpoint be a5, ellipse arc section a1a2Arc midpoint be a6, ellipse arc section a2a3
Arc midpoint be a7, ellipse arc section a3a4Arc midpoint be a8。
Further, b6b8For the transverse of cold air outlet, a6a8For the transverse of cold air inlet, face b6b8a6a8For
Aerofoil profile air film hole crosses the middle section of transverse, b5a5For the wing tip sideline of aerofoil profile air film hole, wing tip sideline b5a5With middle section
b6b8a6a8Between angle be aerofoil profile air film hole angle of flare β, angle of flare β be 10 °~40 °.
Further, a of cold air inlet1a4Air line distance is less than or equal to the b of cold air outlet1b4Air line distance, to ensure
The high cooling effect and intensity of aerofoil profile air film hole, and meet aerofoil profile air film hole processing technology requirement.
According to another aspect of the present invention, a kind of aerofoil profile air film for being used to process aero-engine hot-end component is additionally provided
The electrode in hole, electrode profile and the profile of above-mentioned aerofoil profile air film hole match, and electrode axial length is more than or equal to aerofoil profile
The axial length of air film hole.
The invention has the advantages that：
The aerofoil profile air film hole of aero-engine hot-end component of the present invention, when cold air flows into aerofoil profile air film from internal cold air path
Kong Hou, due to the change of the hole cross sectional shape from cold air inlet to cold air outlet, cold air gradually extends to both sides so that coverage rate
Product is big, good heat-insulation effect, good cooling results；Simultaneously because the hole thickness of aerofoil profile air film hole is also gradually thinned, on the one hand cause cold
Gas from outlet spray after be easy to be attached on the wall of hot-end component, on the other hand cause cold air enter high-temperature fuel gas speed compared with
It is small, reduce the pneumatic mixing loss of combustion gas and cold air, improve the pneumatic efficiency of turbo blade.In addition, the cold air of aerofoil profile pore structure
The discharge area of outlet be more than cold air inlet inlet area the characteristics of, also cause this pass flow resistance relatively have it is identical enter
The cylindrical hole of open area is small, therefore under identical operating mode, the discharge coefficient in aerofoil profile hole is higher.Obtaining good cooling effect
While with pneumatic efficiency, aerofoil profile air film hole has good processability, can use traditional electric spark or laser boring, manufacture
Processing is simple, efficient.
In addition to objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to figure, the present invention is further detailed explanation.
Brief description of the drawings
The accompanying drawing for forming the part of the application is used for providing a further understanding of the present invention, schematic reality of the invention
Apply example and its illustrate to be used to explain the present invention, do not form inappropriate limitation of the present invention.In the accompanying drawings：
Fig. 1 is the structural representation of the aerofoil profile air film hole of the aero-engine hot-end component of the preferred embodiment of the present invention；
Fig. 2 is the plan structure signal of the aerofoil profile air film hole of the aero-engine hot-end component of the preferred embodiment of the present invention
Figure；
Fig. 3 is the side view structure signal of the aerofoil profile air film hole of the aero-engine hot-end component of the preferred embodiment of the present invention
Figure；
Fig. 4 is the electrode for being used to process the aerofoil profile air film hole of aero-engine hot-end component of the preferred embodiment of the present invention
Structural representation.
Marginal data：
1st, cold air inlet；101st, the first oval aperture；2nd, cold air outlet；201st, rectangular side foramen alare；202nd, second is oval
Shape hole；203rd, arc-shaped transition；3rd, hot-end component.
Embodiment
Embodiments of the invention are described in detail below in conjunction with accompanying drawing, but the present invention can be limited by following and
The multitude of different ways of covering is implemented.
Fig. 1 is the structural representation of the aerofoil profile air film hole of the aero-engine hot-end component of the preferred embodiment of the present invention；Fig. 2
It is the overlooking the structure diagram of the aerofoil profile air film hole of the aero-engine hot-end component of the preferred embodiment of the present invention；Fig. 3 is this hair
The side structure schematic view of the aerofoil profile air film hole of the aero-engine hot-end component of bright preferred embodiment；Fig. 4 is of the invention preferred
The structural representation for being used to process the electrode of the aerofoil profile air film hole of aero-engine hot-end component of embodiment.
As depicted in figs. 1 and 2, the aerofoil profile air film hole of the aero-engine hot-end component of the present embodiment, including cold air inlet 1
With cold air outlet 2, centre hole axis and the inclined angle α of the wall body of hot-end component 3 of aerofoil profile air film hole are laid, the hole of aerofoil profile air film hole
Open up to width from cold air inlet 1 to the direction of cold air outlet 2 gradually increase and hole thickness it is gradually thinning, so as to be flowed from cold air inlet 1
The heat that the cold air entered gradually extends to both sides and is attached to after slowing down ejection along gradually thinning cold air outlet 2 outside cold air outlet 2
End pieces 3 flow on outer surface.The aerofoil profile air film hole of aero-engine hot-end component 3 of the present invention, when cold air leads to from internal cold air
After road flows into aerofoil profile air film hole, because from cold air inlet 1, to the change of the hole cross sectional shape of cold air outlet 2, cold air is gradually to two
Side extends so that area coverage is big, good heat-insulation effect, good cooling results；Simultaneously because the hole thickness of aerofoil profile air film hole is also gradual
It is thinned, on the one hand causes cold air to be easy to be attached on the wall of hot-end component 3 after spraying from outlet, on the other hand cold air is entered
Enter that the speed of high-temperature fuel gas is smaller, reduce the pneumatic mixing loss of combustion gas and cold air, improve the pneumatic efficiency of turbo blade.Separately
Outside, the discharge area of the cold air outlet 2 of aerofoil profile pore structure is more than the characteristics of inlet area of cold air inlet 1, also causes this pass
Flow resistance it is small compared with the cylindrical hole with identical inlet area, therefore under identical operating mode, the discharge coefficient in aerofoil profile hole compared with
It is high.While good cooling effect and pneumatic efficiency is obtained, aerofoil profile air film hole has good processability, can use tradition
Electric spark or laser boring, manufacture processing is simple, efficiently.Combustion chamber or turbine cooling of the hot-end component 3 for aero-engine
Blade.
As shown in figures 1 and 3, in the present embodiment, the slanted angle α of the hole axle of aerofoil profile air film hole is 20 °~70 °.Tilt
Angle is excessive, more than 70 ° so that the cold air sprayed from cold air outlet 2 can not be excellently attached to the outer surface of hot-end component, the wing
The axial dimension of type air film hole is small, the route segment that cold air passes through, cold air can not be slowed down so that the gas of combustion gas and cold air
Mixing loss is big.Slanted angle is too small, less than 20 ° so that the hole depth of aerofoil profile air film hole is excessive, causes difficulty of processing big；And
Excessive hole depth can cause the path of cold air flow long, and speed is reduced excessive and can not be ejected into hot-end component, cause every
Thermal effect is poor, and cooling effect is poor, adds energy consumption.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the pass of cold air inlet 1 uses major axis inclining along aerofoil profile air film hole
The first oval aperture 101 that tilted direction is laid.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the pass of cold air outlet 2 is using both sides band rectangular side foramen alare 201
The second slotted eye 202, short-axis direction of the both sides rectangular side foramen alare 201 along the second slotted eye 202 lay and along major axis pair
Claim to lay；Second slotted eye 202 of cold air outlet 2 and the hole shape of the first oval aperture 101 of cold air inlet 1, size with
And cloth set direction is identical.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, the second slotted eye 202 rectangular side foramen alare with both sides respectively
It is arc-shaped transition 203 between 201.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, four angular vertexs of cold air outlet 2 are respectively b1、b2、b3And b4, its
Middle b1With b4In same rectangular side foramen alare 201, rectangular opening side b1b4Midpoint be b5, b2With b3In same rectangular side foramen alare
201, rectangular opening side b2b3Midpoint be b7, b1With b2And b3With b4Corresponding laying respectively on the second elliptical aperture short-axis direction
2 points.b1With b2Between there is the curve point b that arranges successively9、b10、b6、b11And b12, b1b9With b12b2Respectively rectangular side foramen alare
201 rectilinear end hole wall, b9b10With b11b12The respectively transition segmental arc of the slotted eye 202 of rectangular side foramen alare 201 and second, b6
Major axis end points for the second slotted eye 202 and be ellipse arc section b10b11Arc midpoint.b3With b4Between have arrange successively
The curve point b of cloth13、b14、b8、b15And b16, b3b13With b16b4The respectively rectilinear end hole wall of rectangular side foramen alare 201, b13b14With
b15b16The respectively transition segmental arc of the slotted eye 202 of rectangular side foramen alare 201 and second, b8For the length of the second slotted eye 202
Shaft end point and be ellipse arc section b14b15Arc midpoint.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, b1、b2、b3And b4Correspondence in the first oval aperture 101
Entrance summit tie point is respectively a1、a2、a3And a4.Ellipse arc section a1a4Arc midpoint be a5.Ellipse arc section a1a2Arc
Shape midpoint is a6.Ellipse arc section a2a3Arc midpoint be a7.Ellipse arc section a3a4Arc midpoint be a8。
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, b6b8For the transverse of cold air outlet 2, a6a8For cold air inlet
1 transverse.Face b6b8a6a8The middle section of transverse, b are crossed for aerofoil profile air film hole5a5For the wing tip side of aerofoil profile air film hole
Line.Wing tip sideline b5a5With middle section b6b8a6a8Between angle be aerofoil profile air film hole angle of flare β.Angle of flare β be 10 °~
40°.The angle of flare is excessive, more than 40 °, easily causes cold air expanding area excessive, the area coverage that cold air exports from cold air outlet 2
Excessive, output speed is too small, can not be attached at hot-end component outer surface, causes effect of heat insulation poor, cooling effect is poor.
As shown in Figure 1, Figure 2 and Figure 3, in the present embodiment, a of cold air inlet 11a4Air line distance goes out less than or equal to cold air
The b of mouth 21b4Air line distance, to ensure the high cooling effect of aerofoil profile air film hole and intensity, and meet aerofoil profile air film hole machined work
Skill requirement.
As shown in figure 4, the electrode for being used to process the aerofoil profile air film hole of aero-engine hot-end component of the present embodiment.Electrode
Profile and the profile of above-mentioned aerofoil profile air film hole match, and electrode axial length is more than or equal to the axial direction length of aerofoil profile air film hole
Degree.
During implementation, there is provided a kind of aerofoil profile air film hole of aero-engine hot-end component, the air film hole can make combustion chamber and whirlpool
Impeller blade wall surface temperature is evenly distributed, thermal stress is small.
Aerofoil profile air film hole, aerofoil profile film hole structure schematic diagram are provided with combustion chamber or turbine cooling blade (hot-end component 3)
As shown in figure 1, its feature structure is：Folder between the center line of aerofoil profile air film hole and combustion chamber or the wall of turbine cooling blade
Angle is α (span is 20 °~70 °), and the cold air inlet 1 of aerofoil profile air film hole is oval, the cold air outlet 2 of aerofoil profile air film hole
Locate to be smoothly transitted, ultimately formed by aerofoil profile air film with circular arc with rectangle for oval and symmetrical both sides rectangle, ellipse
The ellipse of the cold air inlet 1 in hole adds the variable cross-section shape aerofoil profile air film hole of rectangle to the ellipse of cold air outlet 2.From overlook direction
See, the exhibition of aerofoil profile air film hole is become larger to width by cold air inlet 1 to cold air outlet 2, and rectangle is gradually extended in oval both sides
Outlet, while the ellipse at cold air inlet 1 and the ellipse at cold air outlet 2, i.e. the area of cold air outlet 2 of aerofoil profile air film hole
More than the area of cold air inlet 1, which forms the exhibition of aerofoil profile air film hole to the characteristics of expansion, aerofoil profile air film hole top view such as Fig. 2
It is shown.In terms of preceding apparent direction, aerofoil profile air film hole keeps ellipse from cold air inlet 1 to cold air outlet 2.
The isometric views of aerofoil profile film hole structure are as shown in figure 3, a in figure1、a2、a3、a4For entrance ellipse summit, a5, a6,
a7, a8Respectively circular arc a1a4、a1a2、a2a3、a3a4Midpoint, straight line a5a7For the short axle that entrance is oval, straight line a6a8It is ellipse for entrance
Round major axis；b1、b2、b3、b4For egress vertices, b6、b9、b10、b11、b12For curve b1b2On point, wherein b1b9、b2b12For song
Line b1b2On straightway, b10b11For curve b1b2On oval section, b9b10、b11b12For curve b1b2Upper straightway and oval section
Arc transition section, b6For oval section b10b11Midpoint；b8、b13、b14、b15、b16For curve b3b4On point, wherein b3b13、
b4b16For curve b3b4On straightway, b14b15For curve b3b4On oval section, b13b14、b15b16For curve b3b4Upper straightway
With the arc transition section of oval section, b8For oval section b10b11Midpoint, straight line b6b8For the major axis that outlet is oval.Face a6-a8-b8-
b6-a6To cross the middle section of transverse, straight line a5b5With hole middle section a6-a8-b8-b6-a6Angle be aerofoil profile hole the angle of flare
β (span is 10 °~40 °)；Face a5-a7-b7-b5-a5To cross the middle section of ellipse short shaft.
In order to reach the high cooling effect of new theoretical irregularly-shaped hole (the two-dimensional slot type hole, the two dimension seam type hole that such as simulate),
The intensity and processing technology sex chromosome mosaicism of new theoretical irregularly-shaped hole are overcome simultaneously, and aerofoil profile air film hole has special structural requirement：Cold air
Point a in 1 oval section of entrance1With point a4Air line distance a1-a4It is necessarily equal to or less than the point b at cold air outlet 21With point b4's
Air line distance b1-b4, could so use novel electrode as shown in Figure 4 to process aerofoil profile air film hole.
The aerofoil profile air film hole of aero-engine hot-end component of the present invention, specific unique aerofoil profile film hole structure；Aerofoil profile gas
Fenestra is gradually transitions the oval plus symmetrical rectangle in both sides by ellipse, while can be machined using novel electrode.Work as cold air
After internal cold air path flows into aerofoil profile air film hole, due to the change of hole cross sectional shape, cold air gradually extends to both sides so that covers
Capping product is big, good heat-insulation effect, good cooling results；Thickness is also gradually thinned simultaneously, after on the one hand cold air being sprayed from outlet
Be easy to be attached on wall, on the other hand cause cold air enter high-temperature fuel gas speed it is smaller, reduce the pneumatic of combustion gas and cold air
Mixing loss, improve the pneumatic efficiency of turbo blade.The characteristics of discharge area of other aerofoil profile pore structure is more than inlet area,
So that the flow resistance of this pass is small compared with the cylindrical hole with identical inlet area, therefore under identical operating mode, aerofoil profile hole
Discharge coefficient is higher.While good cooling effect and pneumatic efficiency is obtained, aerofoil profile air film hole has good processability,
Traditional electric spark or laser boring can be used, manufacture processing is simply, efficiently.
With Coanda effect and Newton's third law, Three-dimensional numerical calculation, knot are carried out to aerofoil profile air film hole of the present invention
Fruit shows that the film overcast area that aerofoil profile air film hole is formed is big, be evenly distributed, mixing loss is small, good cooling results, can be effective
The temperature for reducing combustion chamber and turbo blade, combustion chamber and turbine blade life requirement can be better met.
The preferred embodiments of the present invention are the foregoing is only, are not intended to limit the invention, for the skill of this area
For art personnel, the present invention can have various modifications and variations.Within the spirit and principles of the invention, that is made any repaiies
Change, equivalent substitution, improvement etc., should be included in the scope of the protection.
Claims (10)
1. a kind of aerofoil profile air film hole of aero-engine hot-end component, including cold air inlet (1) and cold air outlet (2),
Characterized in that,
The centre hole axis of aerofoil profile air film hole are laid with the inclined angle α of hot-end component (3) wall body,
The Kong Zhanxiang width of aerofoil profile air film hole gradually increases from the cold air inlet (1) to the cold air outlet (2) direction and hole
Thickness is gradually thinning, so that the cold air flowed into from the cold air inlet (1) gradually extends to both sides and along described in gradually thinning
Cold air outlet (2) deceleration is attached on the hot-end component (3) outer surface of the cold air outlet (2) outside after spraying to be flowed.
2. the aerofoil profile air film hole of aero-engine hot-end component according to claim 1, it is characterised in that
The slanted angle α of the hole axle of the aerofoil profile air film hole is 20 °~70 °.
3. the aerofoil profile air film hole of aero-engine hot-end component according to claim 2, it is characterised in that
The first oval aperture that the pass of the cold air inlet (1) is laid using incline direction of the major axis along aerofoil profile air film hole
(101)。
4. the aerofoil profile air film hole of aero-engine hot-end component according to claim 3, it is characterised in that
The pass of the cold air outlet (2) uses second slotted eye (202) of the both sides with rectangular side foramen alare (201),
Short-axis direction of the rectangular side foramen alare (201) described in both sides along second slotted eye (202) is laid and along long axial symmetry
Lay；
Second slotted eye (202) of the cold air outlet (2) and first ellipse of the cold air inlet (1) are opened
The hole shape in hole (101), size and cloth set direction are identical.
5. the aerofoil profile air film hole of aero-engine hot-end component according to claim 4, it is characterised in that
Second slotted eye (202) is respectively arc-shaped transition (203) between the rectangular side foramen alare (201) of both sides.
6. the aerofoil profile air film hole of aero-engine hot-end component according to claim 5, it is characterised in that
Four angular vertexs of the cold air outlet (2) are respectively b1、b2、b3And b4, wherein b1With b4In same rectangular side foramen alare
(201),
Rectangular opening side b1b4Midpoint be b5, b2With b3In same rectangular side foramen alare (201), rectangular opening side b2b3Midpoint be b7,
b1With b2And b3With b4Corresponding 2 points laid respectively on the second elliptical aperture short-axis direction；
b1With b2Between there is the curve point b that arranges successively9、b10、b6、b11And b12,
b1b9With b12b2The respectively rectilinear end hole wall of rectangular side foramen alare (201),
b9b10With b11b12The respectively transition segmental arc of rectangular side foramen alare (201) and the second slotted eye (202),
b6Major axis end points for the second slotted eye (202) and be ellipse arc section b10b11Arc midpoint；
b3With b4Between there is the curve point b that arranges successively13、b14、b8、b15And b16, b3b13With b16b4Respectively rectangular side foramen alare
(201) rectilinear end hole wall,
b13b14With b15b16The respectively transition segmental arc of rectangular side foramen alare (201) and the second slotted eye (202),
b8Major axis end points for the second slotted eye (202) and be ellipse arc section b14b15Arc midpoint.
7. the aerofoil profile air film hole of aero-engine hot-end component according to claim 6, it is characterised in that
b1、b2、b3And b4Corresponding entrance summit tie point in the first oval aperture (101) is respectively a1、a2、a3And a4,
Ellipse arc section a1a4Arc midpoint be a5,
Ellipse arc section a1a2Arc midpoint be a6,
Ellipse arc section a2a3Arc midpoint be a7,
Ellipse arc section a3a4Arc midpoint be a8。
8. the aerofoil profile air film hole of aero-engine hot-end component according to claim 7, it is characterised in that
b6b8For the transverse of cold air outlet (2),
a6a8For the transverse of cold air inlet (1),
Face b6b8a6a8The middle section of transverse is crossed for aerofoil profile air film hole,
b5a5For the wing tip sideline of aerofoil profile air film hole,
Wing tip sideline b5a5With middle section b6b8a6a8Between angle be aerofoil profile air film hole angle of flare β, angle of flare β be 10 °~
40°。
9. the aerofoil profile air film hole of aero-engine hot-end component according to claim 8, it is characterised in that
The a of cold air inlet (1)1a4Air line distance is less than or equal to the b of cold air outlet (2)1b4Air line distance, to ensure aerofoil profile air film
The high cooling effect and intensity in hole, and meet aerofoil profile air film hole processing technology requirement.
A kind of 10. electrode for being used to process the aerofoil profile air film hole of aero-engine hot-end component, it is characterised in that
Electrode profile and the profile of the aerofoil profile air film hole any one of claim 1 to 9 match, and electrode is axially long
Axial length of the degree more than or equal to aerofoil profile air film hole.
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110388235A (en) * | 2018-04-18 | 2019-10-29 | 宁波大艾激光科技有限公司 | Material, its processing method and application with shaped air film pore structure |
| CN113027537A (en) * | 2021-03-11 | 2021-06-25 | 河北工业大学 | Air film hole structure and turbine blade |
| CN114985852A (en) * | 2022-06-30 | 2022-09-02 | 贵州安吉华元科技发展有限公司 | Machining method for special-shaped air film hole of aircraft engine blade |
| CN115203862A (en) * | 2022-09-14 | 2022-10-18 | 中国航发四川燃气涡轮研究院 | Air film hole design method based on volume density distribution |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86108819A (en) * | 1985-12-23 | 1987-07-08 | 联合工艺公司 | The electrode of machining film coding passages |
| US20100172762A1 (en) * | 2009-01-07 | 2010-07-08 | Rolls-Royce Plc | Aerofoil |
| CN102953767A (en) * | 2012-11-05 | 2013-03-06 | 西安交通大学 | High-temperature turbine blade-cooling system |
| CN104364581A (en) * | 2012-06-13 | 2015-02-18 | 通用电气公司 | Gas turbine engine wall |
| CN106401654A (en) * | 2016-10-31 | 2017-02-15 | 中国科学院工程热物理研究所 | Disperse air film cooling hole structure |
| CN106437866A (en) * | 2016-10-31 | 2017-02-22 | 中国科学院工程热物理研究所 | Discrete gas film cooling hole structure |
-
2017
- 2017-04-28 CN CN201710293032.9A patent/CN107725115B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86108819A (en) * | 1985-12-23 | 1987-07-08 | 联合工艺公司 | The electrode of machining film coding passages |
| US20100172762A1 (en) * | 2009-01-07 | 2010-07-08 | Rolls-Royce Plc | Aerofoil |
| CN104364581A (en) * | 2012-06-13 | 2015-02-18 | 通用电气公司 | Gas turbine engine wall |
| CN102953767A (en) * | 2012-11-05 | 2013-03-06 | 西安交通大学 | High-temperature turbine blade-cooling system |
| CN106401654A (en) * | 2016-10-31 | 2017-02-15 | 中国科学院工程热物理研究所 | Disperse air film cooling hole structure |
| CN106437866A (en) * | 2016-10-31 | 2017-02-22 | 中国科学院工程热物理研究所 | Discrete gas film cooling hole structure |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110388235A (en) * | 2018-04-18 | 2019-10-29 | 宁波大艾激光科技有限公司 | Material, its processing method and application with shaped air film pore structure |
| CN113027537A (en) * | 2021-03-11 | 2021-06-25 | 河北工业大学 | Air film hole structure and turbine blade |
| CN114985852A (en) * | 2022-06-30 | 2022-09-02 | 贵州安吉华元科技发展有限公司 | Machining method for special-shaped air film hole of aircraft engine blade |
| CN115203862A (en) * | 2022-09-14 | 2022-10-18 | 中国航发四川燃气涡轮研究院 | Air film hole design method based on volume density distribution |
| CN115203862B (en) * | 2022-09-14 | 2022-12-20 | 中国航发四川燃气涡轮研究院 | Air film hole design method based on volume density distribution |
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