CN104736797A - An aerofoil and a method for construction thereof - Google Patents
An aerofoil and a method for construction thereof Download PDFInfo
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- CN104736797A CN104736797A CN201380057078.0A CN201380057078A CN104736797A CN 104736797 A CN104736797 A CN 104736797A CN 201380057078 A CN201380057078 A CN 201380057078A CN 104736797 A CN104736797 A CN 104736797A
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- China
- Prior art keywords
- wall
- inwall
- projection
- coolant fluid
- aerofoil profile
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Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
- F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
- F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape
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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
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/187—Convection cooling
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2260/00—Function
- F05B2260/20—Heat transfer, e.g. cooling
- F05B2260/221—Improvement of heat transfer
- F05B2260/222—Improvement of heat transfer by creating turbulence
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
- Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
- Y10T29/00—Metal working
- Y10T29/49—Method of mechanical manufacture
- Y10T29/49316—Impeller making
- Y10T29/49336—Blade making
Abstract
The present invention relates to an aerofoil (10) and a method for construction of the aerofoil (10). The aerofoil (10) comprises an outer wall (20) and an inner wall (30), wherein the walls (20, 30) are separated by a cooling channel (40), and a coolant fluid (60) is guidable through the cooling channel (40) during the operation of the aerofoil (10). The inner wall (30) is provided with a protrusion (70), which is profiled and arranged such that it extends from the inner wall (30) into the cooling channel (40). The protrusion (70) directs at least a part of the coolant fluid (60) to impinge the coolant fluid (60) on a first region (64) of the outer wall (20).
Description
Technical field
The present invention relates to a kind of aerofoil profile and the method for constructing this aerofoil profile.
Background technique
Aerofoil profile is often used as winged petiole in turbo-machine (such as the combustion gas turbine that generates electricity or steam turbine) and/or blade.Turbo-machine work reaches long time section, and the working fluid (more than 1000 DEG C) in the gas and turbo-machine of its duration of work aerofoil profile and unusual high-temperature contacts.So the temperature of aerofoil profile outer surface greatly raises.Aerofoil profile is exposed to high operating temperature and reaches the so long time period, causes shorten the working life of aerofoil profile.Therefore, this aerofoil profile need be cooled at its duration of work, thus extends its working life.
Impinging cooling is the common technique for making aerofoil profile cool.In impinging cooling, coolant fluid under high pressure strikes on some region (focus) of the aerofoil profile that need cool.This requires to utilize high pressure to provide coolant fluid and impacts to be formed, and this requires to use extra device to increase coolant fluid pressure.Therefore, current impinging cooling technology for make aerofoil profile cool speech be costliness and be not efficient.
US5704763 discloses a kind of aerofoil profile with the coolant path of segmentation, and it comprises the device for the formation of the turbulent flow making the directed cooling fluid through path.These turbulent flows improve cooling effectiveness.
US7722327 proposes a kind of alternative technology for cooling aerofoil profile, and describes the multiple eddy current cooling circuits for thin airfoil, and wherein the wall of aerofoil profile is made up of the multiple independent eddy current cooling channel being connected to leading edge cooling-air supply passage.But this is very expensive solution, because it needs complicated airfoil structure, increase the complexity of structure aerofoil profile thus.
Summary of the invention
The object of the invention is to propose a kind of comparatively simple and Airfoil Design strengthened, for improving the cooling effectiveness of aerofoil profile.
Above-mentioned purpose is realized by aerofoil profile according to claim 1 and method for constructing described aerofoil profile according to claim 11.
Basic object of the present invention proposes a kind of design for aerofoil profile, and the cooling of aerofoil profile (particularly at the duration of work of aerofoil profile) is enhanced.In this article, aerofoil profile according to the present invention comprises outer wall, inwall and the cooling channel between aforesaid wall.The object of cooling channel guides coolant fluid at the duration of work of aerofoil profile.Inwall comprises projection, and this projection extends to cooling channel from inner wall surface.This projection is arranged and determines that profile is to guide (its just flowing over cooling channel and particularly above projection) at least partially of coolant fluid, thus coolant fluid is impacted in the firstth district of outer wall.
Projection contributes to guiding coolant fluid thus forms the impact of coolant fluid on outer wall.The object of the impact of coolant fluid on outer wall is delivered to coolant fluid from outer wall, compared with the routine techniques particularly cooled with convection current by more heat.In addition, by arranging projection, adding the effective surface area of wall, strengthening the heat trnasfer from outer wall to coolant fluid thus.Realize the cooling, the particularly cooling in the firstth district of the outer wall strengthened thus.
According to embodiments of the invention disclosed herein, extend in the flow direction of the projection on inwall at coolant fluid and the direction towards outer wall.
According to an alternative embodiment of the invention disclosed herein, when understanding in the overall flow direction at coolant fluid, projection comprises riser portions, falling portion and peak.Riser portions is rising in the direction of outer wall, and falling portion is declining in the direction of inwall.Peak is between riser portions and falling portion.In addition, the absolute value of the gradient of falling portion is greater than the absolute value of the gradient of riser portions.
This profile according to the projection of previous embodiment is favourable for guiding glibly on coolant fluid to the firstth district on outer wall.The gradient of riser portions guides coolant fluid, to a certain extent to improve the efficiency of coolant fluid to the impact on first of outer wall along riser portions glibly.So, realize coolant fluid accessible circulation in the cooling channel simultaneously and effectively impact.
According to another embodiment of the present invention disclosed herein, the position of projection in aerofoil profile makes projection near the leading edge of aerofoil profile.At the duration of work of aerofoil profile, the leading edge of aerofoil profile stands more to heat than the trailing edge of aerofoil profile.Therefore, by means of making projection be positioned at position closer to leading edge, the object of projection is to make aerofoil profile stand more to add the part cooling of heat, extends the working life of aerofoil profile thus.
According to another embodiment of the present invention disclosed herein, outer wall comprises projection, and this projection extends to cooling channel from the surface of outer wall.Projection on outer wall is also arranged and determines that profile is to guide (its just flowing over cooling channel and above projection particularly on outer wall) at least partially of coolant fluid, thus coolant fluid is impacted in the secondth district of inwall.So, during the inner loop of coolant fluid in cooling channel, likely make the coolant fluid of impact on outer wall change direction and get back on inwall, make coolant fluid prepare again to be directed on outer wall, on the diverse location impacted on outer wall to cause coolant fluid thus.
According to another embodiment of the present invention disclosed herein, extend in the flow direction of the projection on outer wall at coolant fluid and the direction towards inwall.
According to another embodiment of the present invention disclosed herein, when understanding in the overall flow direction at coolant fluid, the projection on outer wall also comprises riser portions, decline and peak.Riser portions is rising in the direction of inwall, and falling portion is declining in the direction of outer wall.Peak is between riser portions and falling portion.In addition, the absolute value of the gradient of falling portion is greater than the absolute value of the gradient of riser portions.
According to any embodiment in previous embodiment, this profile of the projection on outer wall for guiding the coolant fluid impacted on outer wall in the firstth district to get back on inwall glibly, the secondth district is favourable.The gradient of riser portions guides coolant fluid, to a certain extent to improve the efficiency of coolant fluid to the impact on second of inwall along riser portions glibly.So, realize coolant fluid accessible circulation in the cooling channel simultaneously and effectively impact.In addition, this is favourable for a series of impacts caused coolant channel on outer wall, contributes to the cooling effectiveness improving outer wall thus.
According to another embodiment of the present invention disclosed herein, when understanding in the overall flow direction at coolant fluid, the position of projection on outer wall and the position of projection on inwall make to be impacted in the riser portions of the projection on outer wall by the part of the protrusion directs on inwall towards the coolant fluid in the firstth district.So, likely formed coolant fluid in the cooling channel more efficiently and more smooth flow path.
According to another embodiment of the present invention disclosed herein, when understanding in the overall flow direction at coolant fluid, the peak of the projection on the peak of the projection on inwall and outer wall is departed from each other.So this strengthens the fluency of flowing and the efficiency of a series of impacts of coolant fluid between the wall of aerofoil profile.
According to another embodiment of the present invention disclosed herein, the position of projection on outer wall makes it near the leading edge of aerofoil profile.So this is conducive to the cooling of part to being positioned in aerofoil profile near leading edge, because at the duration of work of aerofoil profile, the leading edge of aerofoil profile stands maximum heating.This object is the working life increasing aerofoil profile.
In the method for constructing according to the aerofoil profile of any previous embodiment, outer wall and inwall are arranged such that outer wall is separated with inwall by cooling channel.Be provided with the projection on inwall, the projection on inwall (70) is extended to cooling channel from the surface of inwall.So this is for guiding coolant fluid thus formation coolant fluid is favourable to the impact in the firstth district on outer wall.
Describe now with reference to accompanying drawing of the present invention and relate to a kind of aerofoil profile and of the present invention aforementioned and other embodiment for the method that cools this aerofoil profile.The embodiment illustrated is intended that illustrative, and and unrestricted the present invention.Accompanying drawing comprises following figure, and wherein in whole descriptions and accompanying drawing, identical reference character refers to identical parts.
Accompanying drawing explanation
Other example of the embodiment of the present invention is illustrated in a schematic way in accompanying drawing, wherein:
Fig. 1 shows the sectional view of aerofoil profile according to an embodiment of the invention.
Fig. 2 shows the amplification view of a part of aerofoil profile shown in Fig. 1.
Fig. 3 shows the flow chart of the method for aerofoil profile shown in tectonic maps 1.
Embodiment
The sectional view of the aerofoil profile 10 according to the one or more embodiment of the present invention described herein has been shown in Fig. 1.Aerofoil profile 10 can be such as winged petiole or the blade of the turbo-machine (not shown) of the combustion gas turbine that generates electricity or steam turbine.
Aerofoil profile 10 comprises first wall 20, second wall 30 and cooling channel 40.Cooling channel 40 is between first wall 20 and the second wall 30, and the cooling of the first wall 20 of aerofoil profile 10 is convenient in cooling channel 40.First wall 20 is outer wall and the second wall 30 is inwalls of aerofoil profile 10, and wherein outer wall 20 surrounds inwall 30.In addition, inwall 30 is separated with outer wall 20 by cooling channel 40.According to an illustrative aspects, cooling channel 40 preferably can surround the four corner of inwall 30.But in exemplary aerofoil profile described in this article, inwall 30 is cores of aerofoil profile 10.
At the duration of work of turbo-machine, outer wall 20 is exposed to the heating that hot gas 50 causes outer wall 20 thus, and this improves the temperature of outer wall 20 subsequently.The coolant fluid 60 be assigned in cooling channel 40 flows over cooling channel 40.But the cooling channel 40 be assigned to by coolant fluid 60 in aerofoil profile 10 is the technology be known, and does not contain this technology in this article for simplicity.
When coolant fluid 60 is through cooling channel 40, coolant fluid 60 and the thermo-contact of both outer wall 20 and inwall 30.Inwall 30 is relatively colder compared with outer wall 20.Acting on each other between coolant fluid 60 and outer wall 20 causes the significant heat trnasfer from outer wall 20 to coolant fluid 60, causes the cooling of outer wall 20 thus.Most heat will be removed from aerofoil profile 10 together with coolant fluid 60, as described below.In addition, because coolant fluid 60 contacts with outer wall 20 and inwall 30, so cooling channel 40 can by the heat trnasfer of small quantity on inwall 40.But the major part of hankering being passed to coolant fluid 60 from outer wall 20 is still stayed coolant fluid 60.So, according to aforementioned manner, realize the cooling of outer wall 20.
Any technology that is known can be utilized to be assigned in cooling channel 40 by coolant fluid 60, such as by means of can place of working be connected to be arranged on aerofoil profile 10 base portion or root (not shown) on the coolant fluid feeding member (not shown) of inlet hole 45.Coolant fluid 60 flows over cooling channel 40 afterwards, and coolant fluid 60 eventually passes through the exit orifice 165 that is usually located in the trailing edge 160 of aerofoil profile 10 and leaves.Therefore, by entering into aerofoil profile 10 through inlet hole 45 and passing through to leave through exit orifice 165, coolant fluid 60 is in the inner loop of cooling channel 40.So, utilize the circulating coolant fluid 60 in the cooling channel 40 of aerofoil profile 10, most heat transmitted out from aerofoil profile 10.
With reference to the exemplary aerofoil profile 10 shown in Fig. 1, in the first half 110 of aerofoil profile 10 (above crestal line 100 and near the suction side 130 of aerofoil profile 10), coolant fluid 60 flows towards the leading edge 150 of aerofoil profile 10 usually.On the other hand, in the Lower Half 120 of aerofoil profile 10 (in the below of crestal line 100 and near on the pressure side 140 of aerofoil profile 10), coolant fluid 60 flows towards the trailing edge 160 of aerofoil profile 10 usually.
In order to improve outer wall 20 and for outer wall 20 is cooled coolant fluid 60 between the efficiency of heat trnasfer, the part 35 of inwall 30 comprises multiple projection 70,75.Projection 70,75 on inwall 30 preferably becomes overall with inwall 30.In this article, each projection 70,75 on inwall 30 to extend to from the surface 37 inwall 30 in cooling channel 40 and normally in the direction towards outer wall 20.The circuit of these projections 70, the 75 impact coolant fluid 60 of flowing in cooling channel 40 on inwall.Each projection 70,75 on inwall 30 is arranged and determines that profile is to guide coolant fluid 60 towards the first relative district 64 on outer wall 20, thus in this firstth district 64 that coolant fluid 60 is impacted on outer wall 20.So, obtain the impinging cooling effect to the first relative district 64, because coolant fluid 60 is provided with the pressure of the increase in the first district 64.Coolant fluid 60 this impact to the first district 64 causes the heat trnasfer from the first district 64 outer wall 20 to the enhancing on coolant fluid 60 in this article.Due to the remarkable heating stood at leading edge 150 place of aerofoil profile 10, the part 35 thus comprising the inwall 30 of projection 70,75 is preferably located in the position of the leading edge 150 near aerofoil profile 10.
Similarly, the part 25 of outer wall 20 also comprises multiple projection 80,85, and each projection 80,85 wherein on outer wall 20 to extend to from the surface 27 outer wall 20 in cooling channel 40 and normally in the direction towards inwall 30.Projection 80,85 on outer wall 20 preferably becomes overall with outer wall 20.Each projection 80,85 on outer wall 20 is arranged and determines that profile is to guide towards the second relative district 66 on inwall 30 at least partially by the coolant fluid 60 impacted in the first district 64 on outer wall 20, produce the impinging cooling effect to the second district 66 on inwall 30 thus, so cause the small heat trnasfer from coolant fluid 60 to inwall 30.But most heat is still retained in coolant fluid 60.
In this article, preferably inwall 30 and outer wall 20 comprise respective multiple projections 70,75,80,85, make several corresponding first districts 64 and the second district 66 be present on outer wall 20 and inwall 30, coolant fluid will to be directed on this outer wall 20 and inwall 30 thus to obtain the impinging cooling effect to the first district 64 and the second district 66.
In this article, by arranging multiple projection 70,75,80,85 on inwall 30 and outer wall 20, in cooling channel 40 in the overall flow direction of coolant fluid 60, the coolant fluid through overbump changes direction repeatedly between outer wall 20 and inwall 30.Such as, if the first projection 70,75 is positioned on inwall 30 when looking in overall flow direction, so coolant fluid 60 is directed and impact in the first district 64 on outer wall 20.Afterwards, coolant fluid 60 is made to change direction and the second district 66 relative on inwall 30, so that coolant fluid 60 impacts on inwall 30 further.Afterwards, change direction by again making coolant fluid 60 and towards the first district 64 of outer wall, etc.Especially, this series impact of the outer wall 20 of coolant fluid 60 pairs of aerofoil profiles 10 causes the raising of the cooling effectiveness of aerofoil profile 10.In addition, this part 25 comprising the outer wall 20 of projection 70,75 is preferably located in the position of the leading edge 150 near aerofoil profile 10 again.
In the first half 110 of aerofoil profile 10, the overall flow direction of coolant fluid 60 in the cooling channel 40 of exemplary aerofoil profile 10 as herein described is preferably from trailing edge towards the direction of leading edge 150.But the local flow direction of coolant fluid 60 is that the profile of each projection 70,75,80,85 flowed in the above by coolant fluid 60 determined.
With reference to Fig. 2, the sample portion 65 of the part 25,35 describing outer wall 20 described hereinbefore and inwall 30 and the aerofoil profile 10 that is present in the cooling channel 40 between part 25,35 and wall 20,30 is illustrated.Due to the flowing above the projection 70,75 of coolant fluid 60 on the inwall 30 of part 65, thus there is coolant fluid 60 to a series of impacts of the outer wall 20 of part 65.Similarly, due to the flowing above the projection 80,85 of coolant fluid 60 on the outer wall 20 of part 65, thus there is coolant fluid 60 to a series of impacts of the inwall 30 of part 65.Now, will in the following paragraphs, coolant fluid 60 is guided to the geometrical shape of projection 70,75, the flow of coolant fluid 60 and projection 70,75 thus causes coolant fluid 60 to be illustrated for the mode making outer wall 20 and cool respective outer wall 20 and the first district 64 of inwall 30 and the impact in the second district 66.
The amplification view of the aforementioned exemplary part 65 of the part 25 of the outer wall 20 comprising aerofoil profile 10 and the part 35 of inwall 30 has been shown in Fig. 2.
More near the leading edge 150 of aerofoil profile 10 when sample portion 65 described is herein arranged in the first half 110 of aerofoil profile 10 and compares with the trailing edge 160 of aerofoil profile 10.Be included in the cooling channel 40 in illustrated part 65, the overall flow direction of coolant fluid 60 is in from trailing edge 160 towards the direction of leading edge 150.
In order to the object of illustrated example part 65, and consider two exemplary protrusions 70,75 in the part 35 of two exemplary protrusions 80,85 in the part 25 of the outer wall 20 of aerofoil profile 10 and inwall 30.When looking along the overall flow direction of the coolant fluid 60 in part 65, each aforementioned projection 70,75,80,85 comprises with lower part:
1. riser portions 170,
2. peak 175, and
3. falling portion 180.
When looking along the overall flow direction of coolant fluid 60, the riser portions 170 of the respective projection 70,75 on inwall 30 extends from the surface 37 inwall 30 and rises in the direction towards outer wall 20, and the riser portions 170 of projection 80,85 on outer wall 20 extends and rises in the direction towards inwall 30 from the surface 27 outer wall 20.Riser portions 170 is preferably continuous and level and smooth, and each riser portions 170 of each projection 70,75,80,85 ends at the respective peak 175 of respective projection 70,75,80,85.Above the riser portions 170 of each projection 80,85, the coolant fluid 60 of flowing is directed toward the riser portions 170 of the relative projection 70,75 on relative wall 30.Subsequently, this causes coolant fluid 60 to the impact in the second relative district 64 of relative wall 20, causes the heat trnasfer of the enhancing between coolant fluid 60 and relative wall 20 thus.
In addition, the flowing of coolant fluid 60 above the riser portions 170 of projection 70,75 causes the acceleration of coolant fluid 60.So, the speed of coolant fluid 60 is increased.Realize for the larger impact of coolant fluid 60 on the impact of the riser portions 170 of the projection 80,85 in opposite wall 20, this strengthens from wall 20 to the heat trnasfer of coolant fluid 60.
When looking along the overall flow direction of coolant fluid 60, the falling portion 180 of the projection 70,75 on inwall 30 declines from respective peak 175 and the direction towards inwall 30 self, and the falling portion 180 of projection 80,85 on outer wall 20 declines from respective peak 175 and the direction towards outer wall 20 self.
In this article, the absolute value of the respective gradient of the falling portion 180 of each respective projection 70,75,80,85 is preferably more than the absolute value of the gradient of the riser portions 170 of each respective projection 70,75,80,85, and namely riser portions 170 little by little rises and falling portion 180 suddenly declines.
The profile of riser portions 170 can be linear, logarithm, index, quadratic function etc.Similarly, the profile of falling portion 180 can be profile etc. linear, logarithm, index, quadratic function.But the profile of all projections 70,75,80,85 is identical substantially.
The peak 175 of each projection 70,75,80,85 is between the respective riser portions 170 and respective falling portion 180 of projection 70,75,80,85.Projection 70,75,80,85 is zero in the gradient at its peak 175 place.When coolant fluid flows along the riser portions 170 of respective projection 70,75,80,85, the local flow direction of coolant fluid 60 constantly changes.In the direction of the respective opposed area 64,66 impacting the relative wall 20,30 above it towards coolant fluid 60 in the local flow at peak 175 place of respective projection 70,75,80,85.
Depend on the profile of respective projection 70,75,80,85, the flowing of coolant fluid 60 above projection 70,75,80,85 also can form the eddy current of coolant fluid 60.The laminar flow of common coolant fluid 60 is transformed into turbulent flow in this article, is similar to the effect of turbolator, causes better heat trnasfer between the inwall 30 of coolant fluid 60 and aerofoil profile 10 and outer wall 20 thus.
The overall flow direction of coolant fluid 60 is represented in this article with the tangent line " X " 190 tangent with the part 25 of the outer wall 20 be included in part 65.At the peak 175 of the projection 70,75,80,85 shown in part 65 by projecting on tangent line " X " 190 from peak 175 to the decline vertical line tangent line " X " 190, thus at the upper position X forming peak 175 of tangent line " X "
1, X
2, X
3and X
4.At this place, X
1and X
3the position at the peak 175 of exemplary protrusions 80,85 respective on outer wall 20, and wherein X
2and X
4it is the position at the peak 175 of exemplary protrusions 70,75 respective on inwall 30.
Respective projection 70,75,80,85 on any wall 20,30 preferably and be equidistantly substantially each other, namely when identical substantially along distance when looking in the overall flow direction of coolant fluid 60 between the adjacent apices 175 of respective projection 70,75,80,85.Such as, the peak X of projection 80,85
1and X
3distance between 175 is by the distance between any two adjacent apices 175 of respective projection 80,85 of equaling on the outer wall 20 of aerofoil profile 10.In this article, it should be noted that when and the projection 80,85 on outer wall 20 between distance compared with time, the distance between the projection 70,75 on inwall 30 has and slightly changes.This can owing to curvature slightly different between inwall 30 from outer wall 20 and radius.And due to the change in the curvature of inwall 30, the distance between the projection 70,75 on inwall 30 has and slightly changes, and identical reason is also applicable to outer wall 20.But when piecewise is considered, the distance between the respective projection 70,75,80,85 of respective wall 20,30 is identical substantially.
In addition, the projection 70,75 on a wall 30 and the projection 80,85 in opposite wall 20 depart from each other, and namely when looking along the overall flow direction of coolant fluid 60, they are indirectly toward each other.That is, the peak 175 of the projection 80,85 on outer wall 20 and the peak 175 of the projection 70,75 on inwall 30 are preferably indirectly toward each other.Such as, X
1with X
2directly toward each other, and kindred circumstances is applicable to X
3and X
4.In addition, the peak X when looking along tangent line " X " 190
2be positioned at peak X
1and X
3between, be preferably located in peak X
1and X
3centre.Similarly, when tangentially " X " 190 looks, peak X
3be positioned at peak X
2and X
4between, be preferably located in peak X
2and X
4middle.
Relative to the position of the projection 70,75 on inwall 30, the position of the projection 80,85 on outer wall 20 is that the first and second districts 64,66 that coolant fluid 60 is impacted are respective between the peak 175 of the respective projection 70,75,80,85 of respective outer and inner wall 30,20.That is, the first district 64 on outer wall 20 is positioned at the peak X of the projection 80,85 of outer wall 20
1and X
3between 170, and the second district 66 on inwall 30 is positioned at the peak X of the projection 70,75 of inwall 30
2and X
4between 170.
In this article, the independent position of projection 70,75,80,85 is intended that the independent position of projection 70,75,80,85 in the overall flow direction of coolant fluid 60.
Preferably, the first and second districts 64,66 that coolant fluid 60 impacts are respective projections 70,75,80,85 of relative wall 20,30.Particularly, the first district 64 and the second district 66 are riser portions 170 of respective projection 70,75,80,85.Coolant fluid 60 rises along the riser portions 170 of projection 70, and the flow direction of coolant fluid changes at peak 175 place of projection 70,75,80,85.Afterwards, coolant fluid 60 is directed toward the riser portions 170 of the relative projection 80 in its opposite wall 30 of impacting, and causes the heat trnasfer from opposite wall 20 to coolant fluid 60 thus.So aforesaid first district 64 and the second district 66 can be the respective riser portions of respective projection 70,75,80,85.In this article, the impact of coolant fluid 60 pairs of outer walls 30 causes the heat trnasfer from outer wall 20 to coolant fluid 60, and the impact of coolant fluid 60 pairs of inwalls 30 causes the heat trnasfer from coolant fluid 60 to inwall 30.When coolant fluid 60 impacts in projection 70,75,80,85, most heat trnasfer occurs in the riser portions 170 of projection 70,75,80,85 all the time.
In this article, precision casting, laser sintered, electron discharge processing etc. can be utilized projection 70,75,80,85 to be arranged on outer wall 20 and inwall 30.
Fig. 3 shows the flow chart of the method for constructing aerofoil profile 10.
In step 200, the inwall 30 of aerofoil profile 10 and outer wall 20 are arranged to toward each other.The layout of wall 20,30 makes between inwall 30 and outer wall 20, form aforesaid cooling channel 40, and wherein inwall 30 is separated with outer wall 20 by cooling channel 40.
In step 210, inwall 30 arranges and has projection 70,75.Projection 70,75 on inwall 30 extends from surface 37 and also to cooling channel 40, and in the direction towards outer wall 20.In addition, outer wall 20 also arranges and has projection 80,85.Projection 80,85 on outer wall 20 also extends from surface 27 and also to cooling channel 40, and in the direction towards inwall 30.The layout of inwall 30 and outer wall 20 is that the peak 175 of the projection 70,75 of inwall 30 is departed from the flow direction of coolant fluid 60 each other with the peak 175 of the projection 80,85 of outer wall 20.
In this article, can be depending on the region 64 in the accurate opposite wall 20 of impacting of coolant fluid 60, the projection 70,75 on certain wall 30 is arranged on some preposition place, thus the region 64 in opposite wall is cooled.These regions 64 can be the focuses on outer wall 20, and when making aerofoil profile 10 be exposed to hot gas 50, these focuses stand strong heating.These focuses mainly appear at leading edge 150 place in aerofoil profile 10.So the flowing above the projection 70,75,80,85 of coolant fluid 60 on inwall 30 is accurately guided, thus causes coolant fluid to be impacted on focus.
Afterwards, coolant fluid 60 can be distributed in cooling channel 40.In this article, the circuit of coolant fluid 60 in cooling channel 40 is the impact of the profile being subject to the projection 70,75 on inwall 30 and the projection 80,85 on outer wall 20.
On inwall 30, above any projection 70,75, the coolant fluid 60 of flowing is directed toward outer wall 20, causes the impact in the region 64 of coolant fluid 60 pairs of outer walls 20 thus.The impact of coolant fluid 60 pairs of outer walls 20 causes the heat trnasfer from outer wall 20 to coolant fluid 60.So, realize the cooling of outer wall 20.Similarly, above any projection 80,85 on outer wall 20, the coolant fluid 60 of flowing is directed toward inwall 30, causes the impact in the region 66 of coolant fluid 60 pairs of inwalls 30 thus.The impact of coolant fluid 60 pairs of inwalls 30 causes the heat trnasfer from coolant fluid 60 to inwall 30.So, coolant fluid 60 is cooled, thus it is changed again direction to outer wall 20, for the further cooling of outer wall 20.
Although describe the present invention with reference to specific embodiment in this article, this description is not intended to be understood as that to be restrictive.When with reference to description of the invention, the various example of disclosed embodiment of the present invention and alternate embodiments will become clear for those skilled in the art.Therefore, among consideration, this amendment can be made under the prerequisite not departing from the embodiment of the present invention as defined.
Claims (11)
1. an aerofoil profile (10), comprising:
-outer wall (20) and inwall (30), and
-cooling channel (40), described cooling channel (40) are positioned between described outer wall (20) and described inwall (30), guide coolant fluid (60) for the duration of work in described aerofoil profile (10);
Wherein, described inwall (30) comprises the projection (70) extended to from the surface (37) of described inwall (30) described cooling channel (40);
It is characterized in that
Described projection (70) on described inwall (30) is arranged and determines that profile is to make when described coolant fluid (60) is just flowing over described cooling channel (40) and the top of the described projection (70) on described inwall (30), described projection (70) on described inwall (30) guides described coolant fluid (60) at least partially, impacts in firstth district (64) of described outer wall (20) to make described coolant fluid (60).
2. aerofoil profile according to claim 1 (10), wherein, the described projection (70) on described inwall (30) extends in the direction of described outer wall (20) in the flow direction neutralization of described coolant fluid (60).
3. aerofoil profile according to claim 1 and 2 (10), wherein, in the overall flow direction of described coolant fluid (60), the described projection (70) on described inwall (30) comprising:
-riser portions (170), it rises in the direction towards described outer wall (20),
-falling portion (180), it declines in the direction towards described inwall (30), and
-peak (175), it is positioned between described riser portions (170) and described falling portion (180);
Wherein, the absolute value of the gradient of described falling portion (180) is greater than the gradient absolute value of described riser portions (170).
4. aerofoil profile according to any one of claim 1 to 3 (10), wherein, compared with the trailing edge (160) of described aerofoil profile (10), the described projection (70) on described inwall (30) is positioned at the position of the leading edge (150) near described aerofoil profile (10).
5. aerofoil profile according to any one of claim 1 to 4 (10), wherein, described outer wall (20) also comprises projection (80),
Wherein, the described projection (80) on described outer wall (20) extends to described cooling channel (40) from the surface (27) of described outer wall (20), and
Wherein, described projection (80) on described outer wall (20) is arranged and determines that profile is to make when described coolant fluid (60) is just flowing over described cooling channel (40) and the top of the described projection (80) on described outer wall (20), described projection (80) on described outer wall (20) guides described coolant fluid (60) at least partially, to impact in secondth district (66) of described inwall (30).
6. aerofoil profile according to claim 5 (10), wherein, extends in the described flow direction of described projection (80) at described coolant fluid (60) on described outer wall (20) and the direction towards described inwall (30).
7. the aerofoil profile (10) according to claim 5 or 6, wherein, in the described overall flow direction of described coolant fluid (60), the described projection (80) on described outer wall (20) comprising:
-riser portions (170), it rises in the direction towards described inwall (30),
-falling portion (180), it declines in the direction towards described outer wall (20), and
-peak (175), it is positioned between described riser portions (170) and described falling portion (180);
Wherein, for the described projection (80) on described outer wall (20), the absolute value of the gradient of described falling portion (180) is greater than the absolute value of the gradient of described riser portions (170).
8. aerofoil profile according to claim 7 (10), wherein, described projection (80) on described outer wall (20) and the described projection (70) on described inwall (30) are arranged in the described overall flow direction of described coolant fluid (60), and being guided by the described projection (70) on described inwall (80) of coolant fluid (60) is impacted in the described riser portions (170) of the described projection (80) on described outer wall (20) towards the part of described firstth district (64) of described outer wall (20).
9. the aerofoil profile (10) according to claim 7 or 8, wherein, in the described overall flow direction of described coolant fluid (60), the described peak (175) of the described projection (80) on described inwall (30) is departed from each other with the described peak (170) of the described projection (70) on described outer wall (20).
10. aerofoil profile according to claim 9 (10), wherein, the described projection (80) on described outer wall (20) is positioned at the position of the described leading edge (150) near described aerofoil profile (10).
11. 1 kinds for constructing the method for aerofoil profile (10), wherein, described aerofoil profile (10) comprising:
-outer wall (20) and inwall (30) and
-cooling channel (40), described cooling channel (40) is positioned between described outer wall (20) and described inwall (30), described outer wall (20) is separated with described inwall (30) by described cooling channel (40), coolant fluid is guided for the duration of work in described aerofoil profile, wherein, described inwall (30) comprises for guiding the described coolant fluid (60) that makes at least partially of described coolant fluid (60) to impact in firstth district (64) of described outer wall (20) when described coolant fluid (60) is just flowing over described cooling channel (40), and
Wherein, the described projection (70) on described inwall (30) extends to described cooling channel (40) from the surface (37) of described inwall (30),
Described method comprises:
-arrange the step (200) that described outer wall (20) and described inwall (30) make described cooling channel and be separated with described inwall (30) by described outer wall (20);
It is characterized in that:
-described projection (70) is arranged on described inwall (30) makes the described projection (70) on described inwall (30) extend to step (210) described cooling channel (40) from the described surface (37) of described inwall (30).
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| EP12190807.3A EP2728116A1 (en) | 2012-10-31 | 2012-10-31 | An aerofoil and a method for construction thereof |
| EP12190807.3 | 2012-10-31 | ||
| PCT/EP2013/072388 WO2014067869A1 (en) | 2012-10-31 | 2013-10-25 | An aerofoil and a method for construction thereof |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN104736797A true CN104736797A (en) | 2015-06-24 |
Family
ID=47142982
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201380057078.0A Pending CN104736797A (en) | 2012-10-31 | 2013-10-25 | An aerofoil and a method for construction thereof |
Country Status (6)
| Country | Link |
|---|---|
| US (1) | US20150285082A1 (en) |
| EP (2) | EP2728116A1 (en) |
| CN (1) | CN104736797A (en) |
| ES (1) | ES2616411T3 (en) |
| RU (1) | RU2640881C2 (en) |
| WO (1) | WO2014067869A1 (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111852998A (en) * | 2020-06-30 | 2020-10-30 | 江苏大学 | Cavitation suppression wing section device |
| CN114483199A (en) * | 2020-10-23 | 2022-05-13 | 斗山重工业建设有限公司 | Array impingement jet cooling structure with corrugated flow path |
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| US10364683B2 (en) | 2013-11-25 | 2019-07-30 | United Technologies Corporation | Gas turbine engine component cooling passage turbulator |
| US10280841B2 (en) | 2015-12-07 | 2019-05-07 | United Technologies Corporation | Baffle insert for a gas turbine engine component and method of cooling |
| US10422233B2 (en) * | 2015-12-07 | 2019-09-24 | United Technologies Corporation | Baffle insert for a gas turbine engine component and component with baffle insert |
| US10577947B2 (en) | 2015-12-07 | 2020-03-03 | United Technologies Corporation | Baffle insert for a gas turbine engine component |
| US10337334B2 (en) | 2015-12-07 | 2019-07-02 | United Technologies Corporation | Gas turbine engine component with a baffle insert |
| US10370983B2 (en) * | 2017-07-28 | 2019-08-06 | Rolls-Royce Corporation | Endwall cooling system |
| US10526898B2 (en) * | 2017-10-24 | 2020-01-07 | United Technologies Corporation | Airfoil cooling circuit |
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| CN114483199A (en) * | 2020-10-23 | 2022-05-13 | 斗山重工业建设有限公司 | Array impingement jet cooling structure with corrugated flow path |
Also Published As
| Publication number | Publication date |
|---|---|
| WO2014067869A1 (en) | 2014-05-08 |
| RU2015120564A (en) | 2016-12-20 |
| EP2893147A1 (en) | 2015-07-15 |
| RU2640881C2 (en) | 2018-01-12 |
| EP2728116A1 (en) | 2014-05-07 |
| US20150285082A1 (en) | 2015-10-08 |
| ES2616411T3 (en) | 2017-06-13 |
| EP2893147B1 (en) | 2016-11-30 |
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