CN113586165B - Turbine blade with single kerosene cooling channel - Google Patents
Turbine blade with single kerosene cooling channel Download PDFInfo
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- CN113586165B CN113586165B CN202110820765.XA CN202110820765A CN113586165B CN 113586165 B CN113586165 B CN 113586165B CN 202110820765 A CN202110820765 A CN 202110820765A CN 113586165 B CN113586165 B CN 113586165B
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- 238000001816 cooling Methods 0.000 title claims abstract description 107
- 239000003350 kerosene Substances 0.000 title claims abstract description 46
- 230000001174 ascending effect Effects 0.000 claims description 35
- 230000000630 rising effect Effects 0.000 claims description 8
- 238000010586 diagram Methods 0.000 description 18
- 238000012360 testing method Methods 0.000 description 16
- 238000012546 transfer Methods 0.000 description 15
- 239000012530 fluid Substances 0.000 description 12
- 230000000694 effects Effects 0.000 description 11
- 238000004088 simulation Methods 0.000 description 9
- 230000000052 comparative effect Effects 0.000 description 8
- 239000007789 gas Substances 0.000 description 6
- 230000001965 increasing effect Effects 0.000 description 5
- 230000009471 action Effects 0.000 description 4
- 239000002737 fuel gas Substances 0.000 description 4
- 239000000463 material Substances 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- IJGRMHOSHXDMSA-UHFFFAOYSA-N Atomic nitrogen Chemical compound N#N IJGRMHOSHXDMSA-UHFFFAOYSA-N 0.000 description 2
- LFQSCWFLJHTTHZ-UHFFFAOYSA-N Ethanol Chemical compound CCO LFQSCWFLJHTTHZ-UHFFFAOYSA-N 0.000 description 2
- 239000012809 cooling fluid Substances 0.000 description 2
- 238000011161 development Methods 0.000 description 2
- 238000000034 method Methods 0.000 description 2
- 238000012545 processing Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000007664 blowing Methods 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 230000008859 change Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000008878 coupling Effects 0.000 description 1
- 238000010168 coupling process Methods 0.000 description 1
- 238000005859 coupling reaction Methods 0.000 description 1
- 230000002708 enhancing effect Effects 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 238000002844 melting Methods 0.000 description 1
- 230000008018 melting Effects 0.000 description 1
- 229910052757 nitrogen Inorganic materials 0.000 description 1
- 239000007800 oxidant agent Substances 0.000 description 1
- 230000001590 oxidative effect Effects 0.000 description 1
- 230000000704 physical effect Effects 0.000 description 1
- 230000008569 process Effects 0.000 description 1
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- 238000006467 substitution reaction Methods 0.000 description 1
- 230000007704 transition Effects 0.000 description 1
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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
- F01D5/185—Liquid cooling
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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
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The present invention relates to a turbine blade having a single kerosene cooling passage, comprising: the cooling structure comprises a turbine blade body and a cooling channel arranged in the turbine blade body, wherein the turbine blade body comprises a blade top, a blade root and a blade body positioned between the blade top and the blade root, the blade body is formed by enclosing a blade pressure surface and a blade suction surface, and a blade front edge and a blade tail edge are respectively formed at the connection part of the blade pressure surface and the blade suction surface; the cooling channel comprises a plurality of U-shaped channels which are sequentially connected in series, and an inlet and an outlet of the cooling channel are both arranged on the blade top, wherein the inlet is close to the front edge of the blade, and the outlet is close to the tail edge of the blade; the U-shaped channels are sequentially arranged along the arc length direction of the suction surface of the blade. The cooling channel arranged on the turbine blade can effectively reduce the temperature of the blade, and the purpose of uniformly cooling the pressure surface and the suction surface of the blade is achieved.
Description
Technical Field
The invention belongs to the field of gas turbines and aerospace engines, and particularly relates to a turbine blade with a single kerosene cooling channel.
Background
Gas turbines and aerospace engines are important equipment in the energy field, and in order to improve the thermal efficiency and the thrust-weight ratio of the engines, the gas inlet temperature in front of the turbine must be increased. Turbine inlet temperatures have now far exceeded the temperature tolerance range of the vane material. To solve the problem of excessive turbine inlet temperatures, researchers have been working on developing more temperature resistant blade materials, or have been working on developing cooling techniques to solve the problem of excessive inlet temperatures.
Common turbine blade cooling methods include internal convection cooling and external film cooling, and for the internal convection cooling method, a rotary cooling channel is mostly adopted as an internal cooling channel, but the rotary cooling channel is limited by conditions such as limited heat exchange area and insufficient contact between cold air and a hot wall surface, so that the turbine blade is unevenly cooled.
Disclosure of Invention
In order to solve the above-mentioned problems occurring in the prior art, the present invention provides a turbine blade having a single kerosene cooling passage. The technical problem to be solved by the invention is realized by the following technical scheme:
the present invention provides a turbine blade having a single kerosene cooling passage, comprising: a turbine blade body and a cooling channel disposed therein, wherein,
the turbine blade body comprises a blade top, a blade root and a blade body positioned between the blade top and the blade root, wherein the blade body is formed by enclosing a blade pressure surface and a blade suction surface, and a blade leading edge and a blade trailing edge are respectively formed at the joint of the blade pressure surface and the blade suction surface;
the cooling channel comprises a plurality of U-shaped channels which are sequentially connected in series, and an inlet and an outlet of the cooling channel are both arranged on the blade top, wherein the inlet is close to the front edge of the blade, and the outlet is close to the tail edge of the blade;
and the U-shaped channels are sequentially arranged along the arc length direction of the suction surface of the blade.
In one embodiment of the invention, the cooling channel comprises a first U-shaped channel and a second U-shaped channel connected, the first U-shaped channel comprising a first descending portion and a first ascending portion, the second U-shaped channel comprising a second descending portion and a second ascending portion, wherein,
the first end of the first descending part is connected with the inlet, and the second end of the first descending part is connected with the first end of the first ascending part;
the second end of the first ascending part is connected with the first end of the second descending part, the second end of the second descending part is connected with the first end of the second ascending part, and the second end of the second ascending part is connected with the outlet;
the first ascending portion and the second descending portion are connected to form an n-type structure, and the n-type structure is located at a position close to the position where the curvature of the suction surface of the blade is maximum.
In one embodiment of the invention, the cross section of the U-shaped channel is circular, and the diameter of the U-shaped channel is 3-5 mm.
In one embodiment of the invention, the distance between the inlet and the leading edge of the blade and the distance between the outlet and the trailing edge of the blade are both 2.8-3 times the diameter of the U-shaped channel.
In one embodiment of the invention, the distance between the n-shaped structure and the position where the curvature of the suction surface of the blade is the largest is 1-1.5 times the diameter of the U-shaped channel.
In one embodiment of the invention, the distance between the first descending part and the first ascending part and the distance between the second descending part and the second ascending part are both 1.5-2 times the diameter of the U-shaped channel;
the distance between the first ascending part and the second descending part is 1.2-2 times of the diameter of the U-shaped channel.
In one embodiment of the invention, the length of the first descending part and the second ascending part is 4.5-7.5 times the diameter of the U-shaped channel;
the length of the first ascending part and the second descending part is 3.3-5.5 times of the diameter of the U-shaped channel;
the distance between the bottoms of the first U-shaped channel and the second U-shaped channel and the blade root is 0.75-1.5 times of the diameter of the U-shaped channel;
the distance between the top of the n-type structure and the blade top is 0.6-1.2 times of the diameter of the U-shaped channel.
Compared with the prior art, the invention has the beneficial effects that:
1. according to the turbine blade with the single kerosene cooling channel, the cooling channel is arranged in the turbine blade body and comprises the plurality of U-shaped channels which are sequentially connected in series, fluid in the channels is changed in the flowing direction for three times at the position close to the blade top or the blade root, the flowing boundary layer and the thermal boundary layer can be re-developed, the re-development of the boundary layer can lead to the increase of the convection heat transfer coefficient in the single channel, and the effect of heat exchange enhancement is further achieved;
2. the turbine blade with the single kerosene cooling channel forms a channel with an n-shaped structure at the position close to the maximum curvature of the suction surface of the blade, and the channel is arranged at the position because the external convection heat transfer coefficient of the position with the maximum curvature of the suction surface of the blade is larger, so that the temperature at the position can be effectively reduced, and the aim of uniformly cooling the pressure surface and the suction surface of the blade is fulfilled;
3. the turbine blade with the single kerosene cooling channel has the advantages of simple structure, easy processing and small flow resistance.
The foregoing description is only an overview of the technical solutions of the present invention, and in order to make the technical means of the present invention more clearly understood, the present invention may be implemented in accordance with the content of the description, and in order to make the above and other objects, features, and advantages of the present invention more clearly understood, the following preferred embodiments are described in detail with reference to the accompanying drawings.
Drawings
FIG. 1 is a perspective view of a turbine blade having a single kerosene cooling channel provided by an embodiment of the present invention;
FIG. 2 is a schematic structural view of a turbine blade body provided by an embodiment of the present invention;
FIG. 3 is a three-dimensional view of a turbine blade having a single kerosene cooling channel provided by an embodiment of the present invention;
FIG. 4 is a schematic structural diagram of a cooling channel provided by an embodiment of the present invention;
FIG. 5 is a temperature profile of a pressure side and a suction side of a blade provided by an embodiment of the present invention;
FIG. 6 is a velocity vector diagram of a U-shaped channel cross-section provided by an embodiment of the present invention;
FIG. 7 is a surface Knoop number distribution plot of cooling channels at different flow rates provided by embodiments of the present invention;
FIG. 8 is a schematic diagram of a comparative cooling channel provided by an embodiment of the present invention;
FIG. 9 is a blade mid-diameter section temperature profile of a cooling passage provided in accordance with an embodiment of the present invention and a comparative cooling passage;
FIG. 10 is a diagram illustrating the results of simulation and test errors of dimensionless temperature rise of kerosene at the inlet and outlet of a cooling channel according to an embodiment of the present invention;
FIG. 11 is a graph of simulated and experimental error results for dimensionless values of the mean temperature of the surface of the cooling channel structure provided by embodiments of the present invention;
FIG. 12 is a diagram showing the relationship between the kerosene temperature rise and the heat exchange amount in the cooling passage and the kerosene flow rate, according to the embodiment of the present invention.
Detailed Description
To further illustrate the technical means and effects of the present invention adopted to achieve the predetermined objects, a turbine blade with a single kerosene cooling channel according to the present invention will be described in detail with reference to the accompanying drawings and the following detailed description.
The foregoing and other technical matters, features and effects of the present invention will be apparent from the following detailed description of the embodiments, which is to be read in connection with the accompanying drawings. The technical means and effects of the present invention adopted to achieve the predetermined purpose can be more deeply and specifically understood through the description of the specific embodiments, however, the attached drawings are provided for reference and description only and are not used for limiting the technical scheme of the present invention.
Example one
Referring to fig. 1 and fig. 2 in combination, fig. 1 is a perspective view of a turbine blade with a single kerosene cooling channel according to an embodiment of the present invention, and fig. 2 is a structural schematic diagram of a turbine blade body according to an embodiment of the present invention. As shown in the drawings, the turbine blade having a single kerosene cooling passage of the present embodiment includes a turbine blade body 10 and a cooling passage 20 provided inside thereof.
As shown in fig. 2, the turbine blade body 10 includes a blade tip 101, a blade root 102, and a blade body located between the blade tip 101 and the blade root 102, the blade body is enclosed by a blade pressure surface 103 and a blade suction surface 104, and a blade leading edge 105 and a blade trailing edge 106 are respectively formed at a connection position of the blade pressure surface 103 and the blade suction surface 104.
In the present embodiment, the turbine blade body 10 has a height of 30mm and a width of 27.9 mm.
Specifically, the cooling channel 20 includes a plurality of U-shaped channels connected in series in sequence, and an inlet 201 and an outlet 202 of the cooling channel 20 are both disposed on the blade tip 101, where the inlet 201 is close to the blade leading edge 105 and the outlet 202 is close to the blade trailing edge 106; the U-shaped channels are arranged in sequence along the arc length of the blade suction surface 104.
In the present embodiment, the turbine blade body 10 and the cooling passage 20 are each of an axisymmetric structure.
Further, referring to fig. 3 and fig. 4 in combination, fig. 3 is a three-dimensional view of a turbine blade with a single kerosene cooling channel according to an embodiment of the present invention, wherein (a) is a front view, (b) is a right side view, and (c) is a top view; fig. 4 is a schematic structural diagram of a cooling channel according to an embodiment of the present invention, wherein (a) is a perspective view, and (b) is a top view. As shown, in the present embodiment, the cooling channel 20 includes a first U-shaped channel 203 and a second U-shaped channel 204 connected, the first U-shaped channel 203 includes a first descending portion 2031 and a first ascending portion 2032, and the second U-shaped channel 204 includes a second descending portion 2041 and a second ascending portion 2042.
Wherein, the first end of the first descending portion 2031 is connected to the inlet 201, and the second end is connected to the first end of the first ascending portion 2032; the second end of the first ascending portion 2032 is connected to the first end of the second descending portion 2041, the second end of the second descending portion 2041 is connected to the first end of the second ascending portion 2042, and the second end of the second ascending portion 2042 is connected to the outlet 202.
In the present embodiment, since the arc length of the blade suction surface 104 is long, the cooling passage 20 is arranged mainly along the arc length direction of the blade suction surface 104.
Due to the greater curvature of the blade leading edge 105 and the blade trailing edge 106, the first descending portion 2031 of the first U-shaped channel 203 is located and arranged close to the blade leading edge 105, the blade pressure side 103 and the blade suction side 104, and the second ascending portion 2042 of the second U-shaped channel 204 is located and arranged close to the blade trailing edge 106, the blade pressure side 103 and the blade suction side 104.
Further, in the present embodiment, the first rising portion 2032 and the second falling portion 2041 are connected to form an n-type structure, and the n-type structure is located close to the position where the curvature of the blade suction surface 104 is the largest because the positional curvature of the symmetry axis of the blade suction surface 104 is the largest, the front-rear pressure gradient is the largest, transition is easily induced, and the heat transfer coefficient between the blade and the high-temperature gas is increased, so that the passage connecting the first rising portion 2032 and the second falling portion 2041 to form the n-type structure is arranged at the position where the curvature of the blade suction surface 104 is the largest, and the temperature at this position can be effectively lowered, thereby achieving the purpose of uniformly cooling the blade pressure surface 103 and the blade suction surface 104.
It should be noted that the first U-shaped channel 203 and the second U-shaped channel 204 are both vertically arranged along the height direction of the turbine blade body 10.
Furthermore, the section of the U-shaped channel is circular, and the diameter of the U-shaped channel is 3-5 mm.
Further, optionally, the distance between the inlet 201 and the leading edge 105 of the blade, and the distance between the outlet 202 and the trailing edge 106 of the blade are both 2.8-3 times the diameter of the U-shaped channel.
In this embodiment, the diameter of the U-shaped channel is 4mm, and the distance between the inlet 201 and the leading edge 105 of the blade, and the distance between the outlet 202 and the trailing edge 106 of the blade are 2.8 times the diameter of the U-shaped channel.
Further, optionally, the distance between the n-shaped structure and the position where the curvature of the suction surface 104 of the blade is the largest is 1-1.5 times the diameter of the U-shaped channel.
In this embodiment, the distance between the n-type structure and the point where the curvature of the suction surface 104 of the blade is greatest is 1.25 times the diameter of the U-shaped channel.
Further, optionally, the distance between the first descending portion 2031 and the first ascending portion 2032, and the distance between the second descending portion 2041 and the second ascending portion 2042 are each 1.5-2 times the diameter of the U-shaped channel.
In the present embodiment, the distance between the first descending portion 2031 and the first ascending portion 2032 (i.e. the diameter of the turn of the first U-shaped channel 203), and the distance between the second descending portion 2041 and the second ascending portion 2042 (i.e. the distance between the turns of the second U-shaped channel 204), are both 2 times the diameter of the U-shaped channel.
Further, optionally, the distance between the first ascending portion 2032 and the second descending portion 2041 is 1.2-2 times the diameter of the U-shaped channel.
In the present embodiment, the distance between the first ascending portion 2032 and the second descending portion 2041 (i.e., the diameter of the turn of the n-type structure) is 1.6 times the diameter of the U-shaped channel.
Further, optionally, the length of the first descending portion 2031 and the second ascending portion 2042 is 4.5 to 7.5 times the diameter of the U-shaped channel; the length of the first ascending portion 2032 and the second descending portion 2041 is 3.3 to 5.5 times the diameter of the U-shaped channel; the distance between the bottom of the first U-shaped channel 203 and the bottom of the second U-shaped channel 204 and the blade root 102 is 0.75-1.5 times of the diameter of the U-shaped channels; the distance between the top of the n-type structure and the blade tip 101 is 0.6-1.2 times the diameter of the U-shaped channel.
In the present embodiment, the lengths of the first descending portion 2031 and the second ascending portion 2042 (i.e., the length of fig. 3 (b) fig. L1) are 5.75 times the diameter of the U-shaped channel; the lengths of the first rising portion 2032 and the second falling portion 2041 (i.e., the length of fig. 3 (b) of fig. L3) are 4.1 times the diameter of the U-shaped channel;
the distance between the bottom of the first and second U-shaped channels 203, 204 and the blade root 102 (i.e., the length of fig. 3 (b) fig. L2) is 0.75 times the diameter of the U-shaped channel; the distance between the top of the n-type structure and the tip 101 (i.e. the length of fig. 3 (b) fig. L4) is 0.8 times the diameter of the U-shaped channel.
The turbine blade having a single kerosene cooling passage of the present embodiment operates as follows: the cooling fluid enters from the inlet 201, passes through the first U-shaped channel 203 and the second U-shaped channel 204 in sequence, and finally flows out from the outlet 202, in this embodiment, the cooling fluid is kerosene.
According to the turbine blade with the single kerosene cooling channel, the cooling channel is arranged in the turbine blade body and comprises the plurality of U-shaped channels which are sequentially connected in series, fluid in the channel is subjected to three times of flow direction conversion at a position close to the blade top or the blade root, a flow boundary layer and a thermal boundary layer can be re-developed, the re-development of the boundary layer can lead to the increase of the convection heat transfer coefficient in the single channel, and the effect of heat exchange enhancement is further achieved; in addition, a channel with an n-type structure is formed at a position close to the maximum curvature of the suction surface of the blade, and the channel is arranged at the position due to the fact that the external convection heat transfer coefficient of the position with the maximum curvature of the suction surface of the blade is large, so that the temperature of the position can be effectively reduced, and the purpose of uniformly cooling the pressure surface and the suction surface of the blade is achieved.
The turbine blade with the single kerosene cooling channel has the advantages of simple structure, easiness in processing and small flow resistance.
Example two
This example was a simulation experiment to verify the cooling effect of the turbine blade having a single kerosene cooling passage according to the first example.
Specifically, the temperature of the main stream fuel gas is 1000K, the flow rate of the main stream fuel gas is 100g/s, the inlet temperature of the cooling kerosene is 300K, and the flow rate is 5.7 g/s. As shown in fig. 5, fig. 5 is a temperature distribution diagram of a pressure surface and a suction surface of a blade according to an embodiment of the present invention, and it can be seen from the diagram that the cooling effect of the pressure surface and the suction surface of the blade is better, and compared with a main stream gas temperature of 1000K, the temperature of the pressure surface and the suction surface of the blade is reduced by about 200K, and the temperature of the leading edge of the blade is reduced by about 100K.
Further, a velocity vector diagram of a U-shaped channel cross section in the cooling channel is analyzed, please refer to fig. 6, and fig. 6 is a velocity vector diagram of a U-shaped channel cross section provided by an embodiment of the present invention. As can be seen from the figure, the fluid in the front area of the elbow is high in speed and close to the inner wall surface, and the fluid is thrown to the outer wall surface by the action of centrifugal force to generate secondary flow through the elbow area. Through the analysis of the enhanced heat transfer field synergy theory, under the condition of given flow speed and fluid physical properties, the heat exchange strength on the convective heat exchange interface not only depends on the speed field and the temperature gradient field, but also depends on the included angle between the speed field and the temperature gradient field, namely, the heat exchange strength not only depends on the absolute values of the speed field, the temperature gradient field and the included angle field, but also depends on the mutual collocation of the three scalar values. The cooperation of the velocity field and the temperature gradient field in the convective heat transfer can strengthen the heat transfer, and the velocity field and the temperature gradient field cooperate better at the moment.
The synergy of the velocity field and the temperature gradient field is embodied in three aspects:
1) the included angle between the speed and the temperature gradient is as small as possible, and the speed and the temperature gradient are parallel as much as possible;
2) local values of the speed, the temperature gradient and the cosine of the included angle should be simultaneously larger, that is, the value of the speed and the temperature gradient should be larger at a place with a larger cosine of the included angle;
3) the fluid velocity profile and the temperature profile are as uniform as possible (at certain conditions of maximum flow velocity and temperature difference).
The flow velocity of the fluid near the wall surface in the area behind the elbow is reduced, flow vortex is generated, the flow area is reduced, and the velocity of the area near the outer wall surface is higher. Therefore, a high heat transfer area is formed in the area close to the inner wall surface in front of the elbow and the area close to the outer wall surface behind the elbow, and the cooperative included angle of the velocity field and the temperature gradient field is the smallest, so that the heat transfer is facilitated.
Further, referring to fig. 7, fig. 7 is a surface knoop number distribution diagram of the cooling channel under different flow rates provided by the embodiment of the present invention (kerosene flow rates are respectively 10.5g/s, 7.8g/s, 5.7g/s, and 4.1g/s), and it can be seen from the diagram that the total distribution of the knoop number on the surface of the cooling channel is relatively uniform, a high heat transfer zone exists at the turn of the U-shaped channel, and the enhanced increase of the heat transfer coefficient can be seen at all three turns. Because the fluid exchanges heat in the pipe, when the fluid flows through the bent pipe, secondary circulation is generated on the cross section due to centrifugal force, disturbance among the fluids is increased, and the heat exchange effect is enhanced. Strong convection is usually a turbulent energy loss proportional to heat exchange in a certain area. To increase the heat exchange area and enhance heat exchange, the heat exchange channels or tubes are typically made in the form of wound bends. When the velocity boundary layer of the fluid is re-developed, vortex structures are created in this region. Longitudinal vortex induced by the secondary flow in the channel is an accompanying flow which occurs in a direction perpendicular to the main flow, and the accompanying movement is usually much less intense than the main flow, but has a more significant effect on enhancing the heat exchange process. The size, position and frequency of secondary flow can cause the deflection of fluid speed and the pressure change of a flow field, and the secondary flow is controlled by adjusting the geometric shape or other parameters of the section, so that the heat exchange can be further enhanced.
Further, in order to compare with the cooling channel of the present embodiment, a comparative cooling channel is provided, please refer to fig. 8, fig. 8 is a schematic structural diagram of a comparative cooling channel according to an embodiment of the present invention, wherein (a) is a front view, (b) is a right view, (c) is a top view, and (d) is a perspective view, as shown in the drawing, in the comparative cooling channel, the first U-shaped channel and the second U-shaped channel are merged.
Referring to fig. 9, fig. 9 is a sectional temperature distribution diagram of the radial surface of the blade of the cooling channel provided in the embodiment of the present invention and the comparative cooling channel, as shown in the figure, the temperature distribution difference of the blade leading edge of the cooling channel of the embodiment and the comparative cooling channel is small, and the dimensionless temperature ratio of the blade leading edge to the main stream temperature is about 0.95. Because of the characteristics of the blade structure, the leading edge main flow directly impacts, and the heat load is the largest, wherein the temperature is the closest to the main flow temperature. However, the cooling channels of the present embodiment can significantly reduce the surface temperature of the pressure side and the suction side of the blade, and the main reason for the smaller temperature difference of the leading edge is that the cooling channels of the present embodiment and the comparative cooling channels are located at the same distance from the leading edge.
Furthermore, as previously analyzed, the U-shaped channel configuration may provide a localized heat transfer coefficient increase at the bend, thereby promoting an overall heat transfer coefficient increase. Therefore, the cooling channel of the embodiment has the advantages of being capable of evenly distributing pipelines, additionally provided with two-way U-shaped pipelines, and capable of improving the overall heat exchange coefficient and reducing the overall temperature of the blades. Therefore, the cooling channel structure designed by the embodiment can uniformly cool the blades in a certain space range by increasing the number of the bent pipeline, and can ensure a certain cooling effect on the suction surface with a poor cooling effect.
In order to verify the accuracy of the numerical simulation, the turbine blade flow heat exchange experimental data with a single kerosene cooling channel of the present embodiment was tested. The blade cooling experimental device mainly comprises a fuel gas generator, a switching section, a test section, a kerosene cooling loop, a test measuring instrument and the like.
Wherein, the main stream fuel gas is composed of alcohol fuel and oxidant air. The experimental test section is connected with the switching section through a flange, and the experimental test blade is welded in the middle of the experimental section. Temperature and pressure measuring points are respectively arranged at an inlet and an outlet of the experimental section, a temperature measuring point is arranged on the surface of the blade, and a pair of temperature and pressure measuring points are respectively arranged at an inlet and an outlet of the cooling flow. The experimental equipment mainly comprises an air source, an alcohol storage tank, a nitrogen blowing system, a gas generator, a cooling air system, a cooling kerosene system, an adjusting valve and the like, and the experimental instrument mainly comprises a temperature sensor, a pressure transmitter, an orifice plate flowmeter and the like.
Referring to fig. 10, fig. 10 is a diagram of results of simulation and test error of dimensionless values of temperature rise of kerosene at an inlet and an outlet of a cooling channel provided in an embodiment of the present invention, and it can be seen from the diagram that errors of numerical simulation and test can be guaranteed to be within 10% for all working conditions from 3g/s to 10.5 g/s. Larger errors occur in conditions with smaller flow rates, because when the flow rate is smaller, the measurement error of the test may be larger, resulting in larger errors from simulation to test.
Through the experimental measurement of the heat exchange quantity of the inner wall surface, a dimensionless value of the average temperature in the blade cooling channel can be obtained through deduction. Referring to fig. 11, fig. 11 is a graph of simulation and test error results of a dimensionless value of the average surface temperature of the cooling channel structure according to the embodiment of the present invention, as shown in the figure, the heat transfer test data is compared with the numerical value of the numerical simulation, the simulation error value of the dimensionless value of the average surface temperature of the cooling channel is within 10%, the accuracy of the internal and external coupling calculation is verified, and the calculated value is well matched with the test value. In the conventional single-channel cooling structure, the temperature difference between the cooling channel inside the blade and the main flow is about 250K.
Referring to fig. 12, fig. 12 is a diagram showing the relationship between the kerosene temperature rise and the heat exchange amount in the cooling passage and the kerosene flow rate according to the embodiment of the present invention. As can be seen from the figure, the kerosene temperature rise and the kerosene flow are approximately in a linear relationship, the kerosene temperature rise is between 45 ℃ and 100 ℃, and the heat exchange quantity is rapidly increased and gradually becomes slower along with the increase of the kerosene flow.
The kerosene cooling test conditions and the test results of the turbine blade with a single kerosene cooling channel of the embodiment are shown in table 1, it can be seen that the highest temperature of the turbine blade occurs at the leading edge of the blade, and according to the experimental measurement, the temperature difference between the main flow and the leading edge is between 110 and 153K, that is, the turbine blade can reduce the temperature of 110K under the condition of the minimum kerosene flow of 3.2 g/s. In the range of ensuring the melting point temperature of the blade material, the cooling channel of the embodiment is adopted to improve the main stream temperature by 11 percent through kerosene cooling, which has significant meaning for improving the heat efficiency and the thrust-weight ratio of the turbine engine.
TABLE 1 kerosene Cooling test conditions and test results
It is noted that, herein, relational terms such as first and second, and the like may be used solely to distinguish one entity or action from another entity or action without necessarily requiring or implying any actual such relationship or order between such entities or actions. Furthermore, the terms "comprises," "comprising," or any other variation thereof, are intended to cover a non-exclusive inclusion, such that an article or device that comprises a list of elements does not include only those elements but may include other elements not expressly listed. Without further limitation, an element defined by the phrase "comprising an … …" does not exclude the presence of additional like elements in the article or device in which the element is included. The terms "connected" or "coupled" and the like are not restricted to physical or mechanical connections, but may include electrical connections, whether direct or indirect. The directional or positional relationships indicated by "up", "down", "left", "right", etc., are based on the directional or positional relationships shown in the drawings, are merely for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the device or element referred to must have a particular orientation, be constructed and operated in a particular orientation, and therefore should not be taken as limiting the invention.
The foregoing is a more detailed description of the invention in connection with specific preferred embodiments and it is not intended that the invention be limited to these specific details. For those skilled in the art to which the invention pertains, several simple deductions or substitutions can be made without departing from the spirit of the invention, and all shall be considered as belonging to the protection scope of the invention.
Claims (6)
1. A turbine blade having a single kerosene cooling passage, comprising: a turbine blade body (10) and a cooling channel (20) disposed therein, wherein,
the turbine blade body (10) comprises a blade top (101), a blade root (102) and a blade body located between the blade top (101) and the blade root (102), the blade body is formed by enclosing a blade pressure surface (103) and a blade suction surface (104), and a blade leading edge (105) and a blade trailing edge (106) are respectively formed at the connection position of the blade pressure surface (103) and the blade suction surface (104);
the cooling channel (20) comprises a plurality of U-shaped channels which are sequentially connected in series, an inlet (201) and an outlet (202) of the cooling channel (20) are both arranged on the blade top (101), wherein the inlet (201) is close to the blade leading edge (105), and the outlet (202) is close to the blade trailing edge (106);
the U-shaped channels are sequentially arranged along the arc length direction of the suction surface (104) of the blade;
the turbine blade body (10) and the cooling channel (20) are both of an axisymmetrical structure;
the cooling channel (20) comprises a first U-shaped channel (203) and a second U-shaped channel (204) which are connected, the first U-shaped channel (203) comprises a first descending part (2031) and a first ascending part (2032), the second U-shaped channel (204) comprises a second descending part (2041) and a second ascending part (2042), wherein,
a first end of the first descending portion (2031) is connected to the inlet (201), and a second end is connected to a first end of the first ascending portion (2032);
a second end of the first rising portion (2032) is connected to a first end of the second falling portion (2041), a second end of the second falling portion (2041) is connected to a first end of the second rising portion (2042), and a second end of the second rising portion (2042) is connected to the outlet (202);
the first rising portion (2032) and the second falling portion (2041) are connected to form an n-type structure, and the n-type structure is located at a position close to the suction surface (104) of the blade where the curvature is maximum.
2. The turbine blade with a single kerosene cooling passage according to claim 1, wherein said U-shaped passage has a circular cross-section, and the diameter of said U-shaped passage is 3-5 mm.
3. The turbine blade with a single kerosene cooling channel according to claim 1, characterized in that the distance between the inlet (201) and the blade leading edge (105), and the distance between the outlet (202) and the blade trailing edge (106) are each 2.8-3 times the diameter of the U-shaped channel.
4. The turbine blade with a single kerosene cooling passage according to claim 1, characterized in that the distance between said n-type structure and the position where the curvature of said blade suction surface (104) is the largest is 1-1.5 times the diameter of said U-shaped passage.
5. The turbine blade with a single kerosene cooling passage according to claim 1, characterized in that the distance between the first descending portion (2031) and the first ascending portion (2032), and the distance between the second descending portion (2041) and the second ascending portion (2042) are each 1.5-2 times the diameter of the U-shaped passage;
the distance between the first rising portion (2032) and the second falling portion (2041) is 1.2-2 times the diameter of the U-shaped channel.
6. The turbine blade with a single kerosene cooling passage according to claim 1, characterized in that the length of the first descending portion (2031) and the second ascending portion (2042) is 4.5-7.5 times the diameter of the U-shaped passage;
the length of the first ascending part (2032) and the second descending part (2041) is 3.3-5.5 times the diameter of the U-shaped channel;
the distance between the bottom of the first U-shaped channel (203) and the bottom of the second U-shaped channel (204) and the blade root (102) is 0.75-1.5 times of the diameter of the U-shaped channels;
the distance between the top of the n-type structure and the blade top (101) is 0.6-1.2 times of the diameter of the U-shaped channel.
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Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196574A (en) * | 2014-07-15 | 2014-12-10 | 西北工业大学 | Gas turbine cooling blade |
| CN106168143A (en) * | 2016-07-12 | 2016-11-30 | 西安交通大学 | A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket |
| CN106481366A (en) * | 2015-08-28 | 2017-03-08 | 中航商用航空发动机有限责任公司 | Cooling blade and gas turbine |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JPS62271902A (en) * | 1986-01-20 | 1987-11-26 | Hitachi Ltd | Cooled blade for gas turbine |
| JP6345319B1 (en) * | 2017-07-07 | 2018-06-20 | 三菱日立パワーシステムズ株式会社 | Turbine blade and gas turbine |
| JP7096695B2 (en) * | 2018-04-17 | 2022-07-06 | 三菱重工業株式会社 | Turbine blades and gas turbines |
| CN110410158B (en) * | 2019-08-16 | 2022-04-12 | 杭州汽轮动力集团有限公司 | Turbine rotor blade of gas turbine |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104196574A (en) * | 2014-07-15 | 2014-12-10 | 西北工业大学 | Gas turbine cooling blade |
| CN106481366A (en) * | 2015-08-28 | 2017-03-08 | 中航商用航空发动机有限责任公司 | Cooling blade and gas turbine |
| CN106168143A (en) * | 2016-07-12 | 2016-11-30 | 西安交通大学 | A kind of turbine blade trailing edge cooling structure with laterally bleed groove and ball-and-socket |
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