CN103470313B - Turbine blade and turbine with same, and engine - Google Patents
Turbine blade and turbine with same, and engine Download PDFInfo
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- CN103470313B CN103470313B CN201310452739.1A CN201310452739A CN103470313B CN 103470313 B CN103470313 B CN 103470313B CN 201310452739 A CN201310452739 A CN 201310452739A CN 103470313 B CN103470313 B CN 103470313B
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Abstract
The invention discloses a turbine blade and a turbine with same, and an engine. The leading edge of the turbine blade forms a first cavity, and the leading edge of the turbine blade forms a first air inlet communicated with the first cavity; at least one air film hole is respectively formed on the suction surface and the pressure surface of the leading edge of the turbine blade and is communicated with the first cavity, and the middle of the turbine blade forms a second cavity; at least two baffles are arranged in the second cavity to define an S-shaped channel, and the middle of the turbine blade is provided with a second air inlet communicated with the S-shaped channel; the second air inlet is adjacent to the leading edge of the turbine blade, and a plurality of exhaust holes communicated with the S-shaped channel are formed on the pressure surface of the trailing edge of the turbine blade and extend to the direction of the trailing edge. According to the turbine blade provided by the invention, the machining is simple, and the cooling efficiency is high.
Description
Technical field
The present invention relates to aviation machine technical field, especially relate to a kind of turbine blade and there is its turbine, motor.
Background technique
Along with the raising of temperature before aero-turbine, the material of traditional turbine blade can not meet user demand, needs to adopt advanced cooling technology.Cooling technology comprises convection current cooling, impinging cooling and gaseous film control.Convection current cooling refers to cooling-air and imports turbine blade inside through passage, utilizes convection effect to discharge heat.Impinging cooling refers to cooling blast from internal impact to turbine blade internal surface, and it can implement very good cooling action to the impact point of impact.Gaseous film control is referred to cooling-air and is outwards flowed out from turbine blade is inner by the some holes on turbine blade, between hot operation gas and turbine blade surface, form thermal-protective coating.Above-mentioned three kinds of types of cooling appropriately being combined according to practical situations, is the type of cooling that traditional aero engine turbine blades adopts usually.But for undersized turbine blade, due to its leaf higher primary school (turbine blade height is less than 20mm), blade thin (turbine blade tail thickness is 0.5mm), thus cooling gas circuit design space is limited and difficulty of processing is large.
Summary of the invention
The present invention is intended at least to solve one of technical problem existed in prior art.For this reason, one object of the present invention is to propose a kind ofly to process simple and that cooling effectiveness is high turbine blade.
Another object of the present invention is to propose a kind of turbine with above-mentioned turbine blade.
Another object of the present invention is to propose a kind of motor with above-mentioned turbine.
The turbine blade of embodiment according to a first aspect of the present invention, the leading edge of described turbine blade is formed with the first cavity, the leading edge of described turbine blade is formed with the first suction port communicated with described first cavity, and the suction surface of described turbine blade leading edge and pressure side are formed with at least one air film hole respectively, air film hole described at least one communicates with described first cavity, the middle part of described turbine blade is formed with the second cavity, at least two dividing plates are provided with to limit S shape passage in described second cavity, the middle part of described turbine blade has the second suction port communicated with described S shape passage, and the leading edge of the contiguous described turbine blade of described second suction port, the described pressure side at the trailing edge place of described turbine blade is formed with the multiple exhaust ports communicated with described S shape passage, described multiple exhaust port all extends towards the direction of described trailing edge.
According to the turbine blade of the embodiment of the present invention, by arranging the first cavity and air film hole in the leading edge of turbine blade, effectively can reduce the temperature of turbine blade leading edge, by arranging S shape passage at the middle part of turbine blade, and multiple exhaust port is set at the trailing edge of turbine blade, thus significantly reducing the temperature of turbine blade middle-part and trailing edge, the cooling effect of whole turbine blade is obvious.In addition, because the internal structure of turbine blade is simple, thus processing technology difficulty is reduced.
In addition, also following additional technical feature can be had according to turbine blade of the present invention:
According to one embodiment of present invention, be provided with the guide plate around described first cavity sidewalls in described first cavity, described guide plate is formed with multiple impact opening.Thus, by arranging guide plate, the temperature of the metallic matrix of the leading edge of turbine blade effectively can be reduced.
Alternatively, the thickness of described guide plate is 0.25mm, and the distance between the sidewall of described guide plate and described first cavity is 1mm.
Particularly, be formed on described guide plate to described impact opening many rows multiple row, and two adjacent rows or the described impact opening interlaced arrangement of two row.
Alternatively, each described impact opening is circular port and diameter is 0.4mm, and the distance between two adjacent described impact openings is 2mm.Thus, impinging cooling effect can effectively be ensured.
According to one embodiment of present invention, described suction surface and described pressure side are formed with respectively the described air film hole that two row are spaced apart from each other, the distances between the described air film hole of two row are 1.5mm, and the diameter of each described air film hole is 0.3mm.Thus, the cold air passed in the first cavity from the first suction port can be discharged from the air film hole suction surface and pressure side respectively, and forms air film thermal-protective coating on the outer wall of the leading edge of turbine blade, thus effectively protects the leading edge of turbine blade.
According to one embodiment of present invention, described dividing plate is two and described two dividing plates be arranged in parallel, described S shape channel partition is become three first passages communicated successively, second channel and third channels by described two dividing plates, wherein said first passage and described second channel communicate at the root of described turbine blade, and described second channel and described third channel communicate at the top of described turbine blade.Thus, by arranging two dividing plates, turbine blade middle-part temperature is significantly reduced.
Further, multiple flow-disturbing rib be spaced apart from each other is respectively equipped with in described first passage, described second channel and described third channel.Thus, by arranging flow-disturbing rib in each passage, reduce further the temperature of turbine blade middle-part.
Alternatively, multiple described flow-disturbing rib in described first passage, described second channel and described third channel be arranged in parallel respectively, and the flow-disturbing rib in described first passage and the angle between the air flow direction in described first passage are 45 °, flow-disturbing rib in described second channel and the angle between the air flow direction in described second channel are 45 °, and the flow-disturbing rib in described third channel and the angle between the air flow direction in described third channel are 45 °.
Alternatively, the height of each described flow-disturbing rib in described first passage and described second channel is 0.5mm, and the distance between adjacent two described flow-disturbing ribs is 5mm, the height of each described flow-disturbing rib in described third channel is 0.25mm, and the distance between adjacent two described flow-disturbing ribs is 2.5mm.
Further, multiple described exhaust port is parallel to each other and communicate with described third channel respectively.Thus, the cold air flowing through third channel is discharged eventually through exhaust port, and forms air film protection at the trailing edge outer wall of turbine blade.
Further, each described exhaust port is circular port and diameter is 0.5mm, and the distance between two adjacent described exhaust ports is 1mm.Thus, by arranging multiple exhaust port, thus can control flow check through going out the cooled gas flow of peristoma.
Alternatively, the height of described turbine blade is 10mm ~ 20mm, and the trailing edge thickness of described turbine blade is 0.4mm ~ 0.8mm.
The turbine of embodiment according to a second aspect of the present invention, comprises the turbine blade of embodiment according to a first aspect of the present invention.
According to the turbine of the embodiment of the present invention, by arranging the turbine blade of above-mentioned first aspect embodiment, because this turbine blade has good cooling effect, thus effectively extend the operating life of turbine.
The motor of embodiment according to a third aspect of the present invention, comprises the turbine of embodiment according to a second aspect of the present invention.
According to the motor of the embodiment of the present invention, by arranging the turbine of above-mentioned second aspect embodiment, thus effectively improve the overall performance of motor, reducing manufacture cost.
Additional aspect of the present invention and advantage will part provide in the following description, and part will become obvious from the following description, or be recognized by practice of the present invention.
Accompanying drawing explanation
Fig. 1 is the structural representation of turbine blade according to an embodiment of the invention;
Fig. 2 is that the air-flow of the turbine blade shown in Fig. 1 moves towards schematic diagram;
Fig. 3 is another structural representation of the turbine blade shown in Fig. 1;
Fig. 4 is that the air-flow of the first cavity shown in Fig. 3 moves towards schematic diagram;
Fig. 5 is the expansion schematic diagram of the guide plate of the turbine blade shown in Fig. 1.
Reference character:
100: turbine blade;
1: leading edge; 11: the first cavitys; 12: guide plate; 13: impact opening; 14: air film hole;
21: the second cavitys; 22: dividing plate; 221: the first dividing plates; 222: second partition;
23: first passage; 24: second channel; 25: third channel;
26: flow-disturbing rib; 261: the first flow-disturbing ribs; 262: the second flow-disturbing ribs; 263: the three flow-disturbing ribs;
3: trailing edge; 31: exhaust port; 4: suction surface; 5: pressure side.
Embodiment
Be described below in detail embodiments of the invention, the example of described embodiment is shown in the drawings, and wherein same or similar label represents same or similar element or has element that is identical or similar functions from start to finish.Be exemplary below by the embodiment be described with reference to the drawings, be intended to for explaining the present invention, and can not limitation of the present invention be interpreted as.
In describing the invention, it will be appreciated that, term " " center ", " longitudinal direction ", " transverse direction ", " thickness ", " front ", " tail ", " level ", " top ", " end ", " interior ", " outward " etc. instruction orientation or position relationship be based on orientation shown in the drawings or position relationship; be only the present invention for convenience of description and simplified characterization; instead of instruction or imply indication device or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present invention.
In addition, term " first ", " second ", " second " only for describing object, and can not be interpreted as instruction or hint relative importance or imply the quantity indicating indicated technical characteristics.Thus, be limited with " first ", the feature of " second " can express or impliedly comprise one or more these features.In describing the invention, the implication of " multiple " is two or more, unless otherwise expressly limited specifically.
In the present invention, unless otherwise clearly defined and limited, it is removably connect that the term such as term, " being connected ", " connection " should do broad sense reason, or integral; Can be directly be connected, also indirectly can be connected by intermediary, can be the connection of two element internals or the interaction relationship of two elements.For the ordinary skill in the art, above-mentioned term concrete meaning in the present invention can be understood as the case may be.
In the present invention, unless otherwise clearly defined and limited, fisrt feature second feature it " on " or D score can comprise the first and second features and directly contact, also can comprise the first and second features and not be directly contact but by the other characterisation contact between them.And, fisrt feature second feature " on ", " top " and " above " comprise fisrt feature directly over second feature and oblique upper, or only represent that fisrt feature level height is higher than second feature.Fisrt feature second feature " under ", " below " and " below " comprise fisrt feature immediately below second feature and tiltedly below, or only represent that fisrt feature level height is less than second feature.
The turbine blade 100 of embodiment is according to a first aspect of the present invention described below with reference to Fig. 1-Fig. 5.
As Figure 1-Figure 4, the turbine blade 100 of embodiment according to a first aspect of the present invention, the leading edge 1 of this turbine blade 100 is formed with the first cavity 11, the middle part of turbine blade 100 is formed with the second cavity 21, the trailing edge 3 of turbine blade 100 is formed with exhaust port 31.
Particularly, first cavity 11 is formed in leading edge 1 place of turbine blade 100, the leading edge 1 of turbine blade 100 is formed with the first suction port (scheming not shown) communicated with the first cavity 11, and the suction surface 4 of turbine blade 100 leading edge 1 and pressure side 5 are formed with at least one air film hole 14 respectively, at least one air film hole 14 communicates with the first cavity 11.With reference to Fig. 1-Fig. 4, leading edge 1 inside of turbine blade 100 is formed with the first cavity 11 of hollow, the shape of cross section of the first cavity 11 is roughly the same with the shape of cross section of the leading edge 1 of turbine blade 100, and the first cavity 11 extends from the top of leading edge 1 to root (bottom such as shown in Fig. 1), first suction port (scheming not shown) can be formed in the top of leading edge 1, and the first suction port is communicated with the first cavity 11, the suction surface 4 at turbine blade 100 leading edge 1 place and pressure side 5 are all formed with air film hole 14, and each air film hole 14 is all connected with the first cavity 11, such cooled gas such as air can flow into the first cavity 11 from the first suction port, and the inwall impacting the first cavity 11 carries out impinging cooling to turbine blade 100, thus effectively can reduce the temperature of the leading edge 1 of turbine blade 100, and can discharge respectively by the air film hole 14 on suction surface 4 and pressure side 5 with the air after the inwall heat exchange of the first cavity 11, thus form air film thermal-protective coating at the outer wall of leading edge 1, leading edge 1 is protected.
Second cavity 21 is formed in the middle part of turbine blade 100, at least two dividing plates 22 are provided with to limit S shape passage in second cavity 21, the middle part of turbine blade 100 has the second suction port (scheming not shown) communicated with S shape passage, and the leading edge 1 of the contiguous turbine blade 100 of the second suction port.As shown in Figure 1-Figure 3, the middle part of turbine blade 100 is formed with the second cavity 21 of hollow, second suction port (scheming not shown) can be formed in the top in the middle part of turbine blade 100, and the contiguous leading edge 1 of this second suction port is arranged, to pass into cooled gas such as air in the second cavity 21, at least two dividing plates 22 are arranged in the second cavity 21, on the suction surface 4 that the two ends of each dividing plate 22 can be connected to turbine blade 100 and pressure side 5, at least two dividing plates 22 interlaced arrangement in the second cavity 21, particularly, the top of a dividing plate 22 is connected with the top of the second cavity 21 and its root (bottom such as shown in Fig. 1) is spaced apart from each other with the root of the second cavity 21, the root of the dividing plate 22 adjacent with this dividing plate 22 is connected with the root of the second cavity 21 and the top of its top and the second cavity 21 is spaced apart from each other, to ensure cooled gas S-shaped flowing in the second cavity 21.It is to be appreciated that the quantity of dividing plate 22 can be arranged according to actual requirement, to meet actual requirement better.
The pressure side 5 at trailing edge 3 place of turbine blade 100 is formed with the multiple exhaust ports 31 communicated with S shape passage, multiple exhaust port 31 all extends towards the direction of trailing edge 3.As shown in Figure 1-Figure 3, multiple exhaust port 31 is formed on the trailing edge 3 of turbine blade 100, one end of each exhaust port 31 communicates with S shape passage last passage (third channel 25 such as shown in Fig. 1 and Fig. 2) near trailing edge 3, and the other end extends towards the direction of the pressure side 5 at turbine blade 100 trailing edge 3 place.Thus; flow out from exhaust port 31 after flowing through the cooled gas in S shape passage and arriving last passage (third channel 25 such as shown in Fig. 1 and Fig. 2); thus significantly reduce the temperature at turbine blade 100 trailing edge 3 place, and then the trailing edge 3 of turbine blade 100 is protected.In addition, by adopting all right control flow check of hole structure through the flow of the cooled gas of exhaust port 31 at trailing edge 3 place of turbine blade 100.
According to the turbine blade 100 of the embodiment of the present invention, by arranging the first cavity 11 and air film hole 14 in the leading edge 1 of turbine blade 100, effectively can reduce the temperature of turbine blade 100 leading edge 1, by arranging S shape passage at the middle part of turbine blade 100, and multiple exhaust port 31 is set at the trailing edge 3 of turbine blade 100, thus the temperature significantly reduced with trailing edge 3 in the middle part of turbine blade 100, the cooling effect of whole turbine blade 100 is obvious.In addition, because the internal structure of turbine blade 100 is simple, thus processing technology difficulty is reduced.
In one embodiment of the invention, be provided with the guide plate 12 around the first cavity 11 sidewall in the first cavity 11, guide plate 12 be formed with multiple impact opening 13.Such as in the example of fig. 3, guide plate 12 is located in the first cavity 11, and be spaced apart from each other with the sidewall of the first cavity 11, particularly, the shape of cross section of guide plate 12 is roughly the same with the first cavity 11 shape of cross section, and multiple impact opening 13 runs through guide plate 12, after cooled gas flows into the first cavity 11 from the first suction port, through the impact opening 13 on guide plate 12, then can impact on the sidewall of the first cavity 11, then discharged by the air film hole 14 on suction surface 4 and pressure side 5.Thus, by arranging guide plate 12, the temperature of the metallic matrix of the leading edge 1 of turbine blade 100 effectively can be reduced.It is to be appreciated that the quantity of impact opening 13 can be arranged according to actual requirement, to meet actual requirement better.
Alternatively, the thickness of guide plate 12 is 0.25mm, and the distance between guide plate 12 and the sidewall of the first cavity 11 is 1mm.It is to be appreciated that the thickness of guide plate 12 and the distance between guide plate 12 and the sidewall of the first cavity 11 can be arranged according to actual requirement, to meet actual requirement better.
Particularly, impact opening more than 13 is formed on guide plate 12 with arranging multiple row, and two adjacent row or two row impact opening 13 interlaced arrangement.As shown in Figure 5, that is, often arrange impact opening 13 and comprise multiple impact opening 13 be spaced apart from each other in the horizontal, often row impact opening 13 comprises multiple impact opening 13 be spaced apart from each other in the vertical, two adjacent row's impact opening 13 interlaced arrangement, namely the impact opening 13 wherein in a row arrange with another in all impact openings 13 all not on same longitudinal straight line, two adjacent row impact opening 13 interlaced arrangement, all impact openings 13 during the impact opening 13 namely wherein in row arranges with another are not all on same horizontal straight line.Such as show nine row impact openings 13 in the example of hgure 5.
Alternatively, each impact opening 13 is circular port, and the diameter of each impact opening 13 is 0.4mm, and the distance between two adjacent impact openings 13 is 2mm.Thus, impinging cooling effect can effectively be ensured.It is to be appreciated that the shape of impact opening 13, size and the arrangement on guide plate 12 can be arranged according to actual requirement, to meet actual requirement better.
In one embodiment of the invention, suction surface 4 and pressure side 5 are formed with respectively the air film hole 14 that two row are spaced apart from each other.As Figure 1-Figure 4; suction surface 4 is formed with the air film hole 14 that two row are spaced apart from each other; this two row air film hole 14 runs through suction surface 4; pressure side 5 is formed with the air film hole 14 that two row are spaced apart from each other; this two row air film hole 14 runs through pressure side 5; cooled gas such as the air passed in the first cavity 11 from the first suction port like this can be discharged from the air film hole 14 suction surface 4 and pressure side 5 respectively; and form air film thermal-protective coating on the outer wall of the leading edge 1 of turbine blade 100, thus effectively protect the leading edge 1 of turbine blade 100.
Alternatively, the distance between two row air film holes 14 is 1.5mm, and the diameter of each air film hole 14 is 0.3mm.It is to be appreciated that the size of air film hole 14 and the arrangement at leading edge 1 place of turbine blade 100 can be arranged according to actual requirement, to meet actual requirement better.
In one embodiment of the invention, dividing plate 22 is two and two dividing plates 22 be arranged in parallel, S shape channel partition is become three first passages communicated successively 23, second channel 24 and third channel 25 by two dividing plates 22, wherein first passage 23 and second channel 24 communicate at the root (bottom such as shown in Fig. 1) of turbine blade 100, and second channel 24 and third channel 25 communicate at the top of turbine blade 100.Such as in the example of fig. 1 and 2, first dividing plate 221 and second partition 222 are located in the second cavity 21 in parallel with each other, and the second cavity 21 is separated into second partition 222 first passage 23, second channel 24 and the third channel 25 that are communicated with successively by the first dividing plate 221.The root (bottom such as Fig. 1 shown in) of the first dividing plate 221 from the top of turbine blade 100 to turbine blade 100 extends, and be spaced apart from each other with the root of turbine blade 100, thus communicated with the root of second channel 24 at turbine blade 100 by the first passage 23 that the first dividing plate 221 is separated out, second partition 222 extends from the root of turbine blade 100 to the top of turbine blade 100, and be spaced apart from each other with the top of turbine blade 100, thus communicated with the top of third channel 25 at turbine blade 100 by the second channel 24 that second partition 222 is separated out, second suction port is connected with first passage 23, such cooled gas such as air enters first passage 23 from the second suction port, and from the overhead stream of first passage 23 to the root of first passage 23, 180 ° of inflow second channels 24 are turned at the root of the first dividing plate 221, the top of second channel 24 is flowed to again from the root of second channel 24, turn over 180 ° at the top of second partition 222 and enter third channel 25, and from the overhead stream of third channel 25 to the root of third channel 25, thus play the effect reducing turbine blade 100 middle portion temperature.It is to be appreciated that the quantity of dividing plate 22 can be arranged according to actual requirement, to meet actual requirement better.
Further, multiple flow-disturbing rib 26 be spaced apart from each other is respectively equipped with in first passage 23, second channel 24 and third channel 25.As depicted in figs. 1 and 2, the corresponding suction surface 4 of the second cavity 21 and the inwall of pressure side 5 are respectively equipped with multiple flow-disturbing rib 26 be spaced apart from each other, each flow-disturbing rib 26 extends from the inwall of the second cavity 21 towards the direction at the center of the second cavity 21, first flow-disturbing rib 261 is located in first passage 23, and the front end of the first flow-disturbing rib 261 is connected with the inwall of contiguous turbine blade 100 leading edge 1 of the second cavity 21, its tail end is connected with the first dividing plate 221, second flow-disturbing rib 262 is located in second channel 24, and the front end of the second flow-disturbing rib 262 is connected with the first dividing plate 221, its tail end is connected with second partition 222, 3rd flow-disturbing rib 263 is located in third channel 25, and the front end of the 3rd flow-disturbing rib 263 is connected with second partition 222, its tail end is connected with the inwall of contiguous turbine blade 100 trailing edge 3 of the second cavity 21, like this by arranging flow-disturbing rib 26 in each passage, reduce further the temperature in the middle part of turbine blade 100.Alternatively, flow-disturbing rib 26 and turbine blade 100 one-body molded.It is to be appreciated that the arrangement in the second cavity 21 of dividing plate 22 can be arranged according to actual requirement, to meet actual requirement better.
Further, the turning of two adjacent passages can arrange flow-disturbing rib 26, as shown in Figure 1, is provided with flow-disturbing rib 26 at second channel 24 and the turning of third channel 25.
Preferably, multiple flow-disturbing ribs 26 in first passage 23, second channel 24 and third channel 25 be arranged in parallel respectively, and the flow-disturbing rib 26 in first passage 23 and the angle between the air flow direction in first passage 23 are 45 °, flow-disturbing rib 26 in second channel 24 and the angle between the air flow direction in second channel 24 are 45 °, and the flow-disturbing rib 26 in third channel 25 and the angle between the air flow direction in third channel 25 are 45 °.
See figures.1.and.2, air-flow flows through first passage 23 first downwards after entering the second cavity 21, four the first flow-disturbing ribs 261 be parallel to each other are provided with in first passage 23, now the flow direction of air-flow and the first dividing plate 221 almost parallel, angle α between air flow direction in each first flow-disturbing rib 261 and first passage 23 is 45 °, that is, angle between each first flow-disturbing rib 261 and the first dividing plate 221 is 45 °, then, air-flow walks around the root of the first dividing plate 221, and upwards flow through second channel 24, three the second flow-disturbing ribs 262 be parallel to each other are provided with in second channel 24, now the flow direction of air-flow and second partition 222 almost parallel, angle β between air flow direction in each second flow-disturbing rib 262 and second channel 24 is 45 °, that is, angle between each second flow-disturbing rib 262 and second partition 222 is 45 °, then, air-flow walks around the top of second partition 222, and flow through third channel 25 downwards, six the 3rd flow-disturbing ribs 263 be parallel to each other are provided with in third channel 25, now the flow direction of air-flow and second partition 222 almost parallel, angle γ between air flow direction in each 3rd flow-disturbing rib 263 and third channel 25 is 45 °, that is, angle between each 3rd flow-disturbing rib 262 and second partition 222 is 45 °.
Alternatively, as Figure 1-Figure 4, the height h of each first flow-disturbing rib 261 in first passage 23 is 0.5mm, namely the distance between the one end at vicinity second cavity 21 center of the first flow-disturbing rib 261 and one end be connected with the inwall of the second cavity 21 of the first flow-disturbing rib 261 is 0.5mm, and the distance S between two the first flow-disturbing ribs 261 adjacent in first passage 23 is 5mm, the height h of each second flow-disturbing rib 262 in second channel 24 is 0.5mm, namely the distance between the one end at vicinity second cavity 21 center of the second flow-disturbing rib 262 and one end be connected with the inwall of the second cavity 21 of the second flow-disturbing rib 262 is 0.5mm, and the distance S between two the second flow-disturbing ribs 262 adjacent in second channel 24 is 5mm, the height h of each 3rd flow-disturbing rib 263 in third channel 25 is 0.25mm, namely the distance between the one end at vicinity second cavity 21 center of the 3rd flow-disturbing rib 263 and one end be connected with the inwall of the second cavity 21 of the 3rd flow-disturbing rib 263 is 0.5mm, and the distance S between two the 3rd flow-disturbing ribs 263 adjacent in third channel 25 is 2.5mm.
In one embodiment of the invention, multiple exhaust port 31 is parallel to each other and communicate with third channel 25 respectively.Such as in the example of fig. 1 and 2, multiple exhaust port 31 is arranged in parallel and run through the pressure side 5 of turbine blade 100, one end (left end such as shown in Fig. 1) of each exhaust port 31 is connected with third channel 25, and its other end (right-hand member such as shown in Fig. 1) extends towards the direction of the trailing edge 3 of turbine blade 100.Thus, the cooled gas such as air flowing through third channel 25 is discharged eventually through exhaust port 31, and forms air film protection to trailing edge 3 outer wall of turbine blade 100.
Preferably, as shown in figures 1 and 3, each exhaust port 31 is circular port, and the diameter d of each exhaust port 31 is 0.5mm, and the distance k between two adjacent exhaust ports 31 is 1mm.
In one embodiment of the invention, as shown in figures 1 and 3, the height H of turbine blade 100 is 10mm ~ 20mm, and the thickness D of the trailing edge 3 of turbine blade 100 is 0.4mm ~ 0.8mm.
The turbine (scheming not shown) of embodiment, comprises the turbine blade 100 according to the above-mentioned first aspect embodiment of the present invention according to a second aspect of the present invention.
According to the turbine of the embodiment of the present invention, by arranging the turbine blade 100 of above-mentioned first aspect embodiment, this turbine blade 100 has good cooling effect, thus effectively extends the operating life of turbine.
The motor (scheming not shown) of embodiment, comprises the turbine according to the above-mentioned second aspect embodiment of the present invention according to a third aspect of the present invention.
Alternatively, motor is turbine inlet temperature is 1500K ~ 1600K(Kelvin) small turbine engine.
According to the motor of the embodiment of the present invention, by arranging the turbine of above-mentioned second aspect embodiment, thus effectively improve the overall performance of motor, reducing manufacture cost.
In the description of this specification, specific features, structure, material or feature that the description of reference term " embodiment ", " some embodiments ", " example ", " concrete example " or " some examples " etc. means to describe in conjunction with this embodiment or example are contained at least one embodiment of the present invention or example.In this manual, to the schematic representation of above-mentioned term not must for be identical embodiment or example.And the specific features of description, structure, material or feature can combine in an appropriate manner in any one or more embodiment or example.In addition, the different embodiment described in this specification or example can carry out engaging and combining by those skilled in the art.
Although illustrate and describe embodiments of the invention above, be understandable that, above-described embodiment is exemplary, can not be interpreted as limitation of the present invention, and those of ordinary skill in the art can change above-described embodiment within the scope of the invention, revises, replace and modification.
Claims (3)
1. a turbine blade, it is characterized in that, the leading edge of described turbine blade is formed with the first cavity, the leading edge of described turbine blade is formed with the first suction port communicated with described first cavity, the guide plate around described first cavity sidewalls is provided with in described first cavity, described guide plate is formed with multiple impact opening, the thickness of described guide plate is 0.25mm, and the distance between the sidewall of described guide plate and described first cavity is 1mm, be formed on described guide plate to described impact opening many rows multiple row, and two adjacent rows or the described impact opening interlaced arrangement of two row, each described impact opening is circular port and diameter is 0.4mm, distance between two adjacent described impact openings is 2mm, and the suction surface of described turbine blade leading edge and pressure side are formed with at least one air film hole respectively, air film hole described at least one communicates with described first cavity, described suction surface and described pressure side are formed with respectively the described air film hole that two row are spaced apart from each other, distance between the described air film hole of two row is 1.5mm, and the diameter of each described air film hole is 0.3mm,
The middle part of described turbine blade is formed with the second cavity, at least two dividing plates are provided with to limit S shape passage in described second cavity, the middle part of described turbine blade has the second suction port communicated with described S shape passage, and the leading edge of the contiguous described turbine blade of described second suction port, described dividing plate is two and described two dividing plates be arranged in parallel, described S shape channel partition is become three first passages communicated successively by described two dividing plates, second channel and third channel, wherein said first passage and described second channel communicate at the root of described turbine blade, described second channel and described third channel communicate at the top of described turbine blade,
Described first passage, multiple flow-disturbing rib be spaced apart from each other is respectively equipped with in described second channel and described third channel, described first passage, multiple described flow-disturbing rib in described second channel and described third channel be arranged in parallel respectively, and the flow-disturbing rib in described first passage and the angle between the air flow direction in described first passage are 45 °, flow-disturbing rib in described second channel and the angle between the air flow direction in described second channel are 45 °, flow-disturbing rib in described third channel and the angle between the air flow direction in described third channel are 45 °, the height of each described flow-disturbing rib in described first passage and described second channel is 0.5mm, and the distance between adjacent two described flow-disturbing ribs is 5mm, the height of each described flow-disturbing rib in described third channel is 0.25mm, and the distance between adjacent two described flow-disturbing ribs is 2.5mm,
The pressure side at the trailing edge place of described turbine blade is formed with the multiple exhaust ports communicated with described S shape passage, described multiple exhaust port all extends towards the direction of described trailing edge, multiple described exhaust port is parallel to each other and communicate with described third channel respectively, each described exhaust port is circular port and diameter is 0.5mm, distance between two adjacent described exhaust ports is 1mm, the height of described turbine blade is 10mm ~ 20mm, and the trailing edge thickness of described turbine blade is 0.4mm ~ 0.8mm.
2. a turbine, is characterized in that, comprises turbine blade as claimed in claim 1.
3. a motor, is characterized in that, comprises turbine as claimed in claim 2.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310452739.1A CN103470313B (en) | 2013-09-27 | 2013-09-27 | Turbine blade and turbine with same, and engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310452739.1A CN103470313B (en) | 2013-09-27 | 2013-09-27 | Turbine blade and turbine with same, and engine |
Publications (2)
| Publication Number | Publication Date |
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| CN103470313A CN103470313A (en) | 2013-12-25 |
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN104265376B (en) * | 2014-09-22 | 2016-04-06 | 西北工业大学 | A kind of oblique impact jet cooling channel |
| CN106555776B (en) * | 2015-09-25 | 2019-04-12 | 中国航发商用航空发动机有限责任公司 | Turbofan and its fan blade |
| CN109139127A (en) * | 2018-09-17 | 2019-01-04 | 北京航空航天大学 | A kind of pre- rotating gaseous film control structure of turbine guide vane |
| CN111412020A (en) * | 2020-03-30 | 2020-07-14 | 中国科学院工程热物理研究所 | Turbine blade trailing edge cooling structure |
| CN111577397B (en) * | 2020-05-28 | 2022-12-06 | 中国航发湖南动力机械研究所 | Turbine blade and aircraft engine |
| CN112576316B (en) * | 2020-11-16 | 2023-02-21 | 哈尔滨工业大学 | Turbine blade |
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