CN216642214U - High-blockage-ratio finned laminate cooling structure for middle chord area of turbine blade - Google Patents
High-blockage-ratio finned laminate cooling structure for middle chord area of turbine blade Download PDFInfo
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- CN216642214U CN216642214U CN202123293359.7U CN202123293359U CN216642214U CN 216642214 U CN216642214 U CN 216642214U CN 202123293359 U CN202123293359 U CN 202123293359U CN 216642214 U CN216642214 U CN 216642214U
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Abstract
The utility model relates to a cooling structure of a high-blockage-ratio finned plate for a middle chord area of a turbine blade, which comprises a blade double-layer wall positioned in the middle chord of the blade, wherein the blade double-layer wall consists of an air film pore plate, an impact pore plate and an impact airflow cooling channel between the air film pore plate and the impact pore plate, a high-blockage-ratio fin is arranged on the air film pore plate in the impact airflow cooling channel in an extending way along the blade height direction of the turbine blade, and a parallel slit for disturbing and reducing the flow resistance of cooling air is arranged on the high-blockage-ratio fin along the cooling airflow direction. The total heat transfer increases accordingly.
Description
Technical Field
The present invention relates to blade cooling structures, and more particularly to internal cooling structures for mid-chord regions of turbine blades.
Background
The power and efficiency of aircraft engines/gas turbines increases as the turbine inlet gas temperature increases. The turbine inlet temperature of the currently in-service gas turbine engines has exceeded 1850K, far exceeding the thermal endurance limit of blade superalloy materials (1150K), and the turbine inlet temperature of advanced gas turbine engines has shown a tendency to increase, and therefore, in order to ensure safe and reliable operation of turbine blades under high thermal load conditions, efficient cooling measures must be taken.
Impingement-film double-wall cooling techniques have received much attention from researchers because of their fully integrated benefits of both internal impingement cooling and external film cooling. In the impact/air film double-wall air film cooling structure, cold air flows out of impact holes in the impact plate and then generates impact heat exchange with the inner wall surface of the air film plate, so that the heat exchange effect of the area near the stagnation point is obviously improved. Wall efflux then takes place the interact from the gas film hole outflow on the gas film board with mainstream high temperature gas, forms the gas film cooling, avoids high temperature gas and wall direct contact, plays the effect that reduces the temperature of blade surface. Compared with other single traditional methods such as internal convection cooling, impingement cooling and film cooling, the impingement-film cooling technology can provide better cooling performance and higher cooling efficiency.
In order to further improve the internal impact cooling characteristic of the impact-air film double-wall cooling structure, different types of rough turbulence elements, such as turbulence columns, fins and surface-recessed vortex generators, are arranged on a target surface (the inner wall surface of an air film plate). The cooling structure is called as a laminated plate structure, and the arranged turbulence elements not only increase the mixing degree with the cooling gas flowing through the cooling channel, but also increase the surface area for heat exchange, thereby increasing the heat exchange strength of the inner wall surface of the air film plate in the laminated plate structure. In the application of a common laminate cooling structure, the inner wall surface of the air film plate is mainly provided with solid turbulence columns and turbulence ribs with different shapes, blockage ratios, spacing ratios and arrangement modes. The prior literature research shows that the fins with high blocking ratio can effectively weaken the influence of cross flow on impact heat exchange and enhance the overall heat exchange characteristic, but also cause more pressure loss (flow resistance), the cold air in the turbine blades is usually provided by the compressor, and the larger the resistance of the cold air flowing through the cooling unit is, the larger the power loss of the compressor is. Therefore, in order to design a cooling structure having both excellent heat exchange characteristics and a low flow resistance coefficient without increasing the flow rate of cold air, it is important for the safe and stable operation of the blade.
Disclosure of Invention
The utility model aims to avoid the defects of the prior art and provide a turbine blade middle chord area fin plate cooling structure with high blocking ratio under the condition of not increasing cold air flow and simultaneously having excellent heat exchange characteristics and lower flow resistance coefficient.
In order to achieve the purpose, the utility model adopts the technical scheme that: a cooling structure of a high-blocking-ratio ribbed laminate for a middle chord area of a turbine blade comprises a blade double-layer wall positioned at the middle chord of the blade, wherein the blade double-layer wall is composed of an air film pore plate, an impact pore plate and an impact airflow cooling channel, the impact airflow cooling channel is arranged between the air film pore plate and the impact pore plate, the air film pores are uniformly arranged on the air film pore plate at equal intervals, the impact pore plate is uniformly provided with impact pores at equal intervals, and the air film pores and the impact pores are arranged in a staggered manner;
a high-blockage-ratio rib is arranged on an air film pore plate in the impinging stream cooling channel in an extending manner along the blade height direction of the turbine blade, and two ends of the high-blockage-ratio rib are connected to the channel side wall of the impinging stream cooling channel;
parallel slits for disturbing and reducing the flow resistance of cooling gas are arranged on the high blockage ratio fins along the direction of the cooling gas flow, the cooling gas flow flows in from inlets of the parallel slits and flows out from outlets of the parallel slits, and the parallel slits are continuously or intermittently extended and arranged in the extending direction of the high blockage ratio fins; the upper and lower slit surfaces of the parallel slit are arranged in parallel, and the inlet height of the parallel slit is the same as the outlet height of the parallel slit;
the aperture of the impact hole and the aperture of the air film hole are both the aperture d, and the high blocking ratio rib is positioned behind the air film hole along the direction of the cooling air flow, and the distance between the high blocking ratio rib and the air film hole is 1-5 d, namely the distance between the impact hole and the impact target surface.
Further, the impact orifice plate is an air inlet plate and is arranged on the cold air side of the turbine blade; the gas film pore plate is a gas outlet plate and is arranged on the gas side of the turbine blade; the thickness of the impact orifice plate and the thickness of the air film orifice plate are both 0.5-3 d, and the width in the spreading direction is both 4-8 d.
Further, the ratio of the height H of the impingement airflow cooling channel to the aperture d is 0.5-3.
Furthermore, the impact holes and the air film holes are respectively arranged on the impact hole plate and the air film hole plate in a direction perpendicular to the main airflow, the aperture d is 2-10 mm, and the relative distance between each two adjacent impact holes and each air film hole along the airflow direction and the spreading direction is 4-8 d; the staggered interval of the impact holes and the air film holes is 2-4 d.
Furthermore, the hole types of the impact hole and the air film hole are both cylindrical holes.
Furthermore, the cross section of the high blockage ratio rib is square, and the ratio of the height of the high blockage ratio rib to the height H of the impinging stream cooling channel is 0.2-0.5.
Furthermore, the parallel slits are obliquely arranged relative to the airflow flowing direction, the inclination angle alpha is 0-30 degrees, the penetration rate beta is 0.05-0.4 when c is the height of the parallel slits, and e is the height of the high blockage ratio rib.
Further, the blade double-layer wall of the middle chord of the blade comprises a pressure surface and a suction surface.
The utility model has the beneficial effects that: the utility model arranges the high-blockage-ratio rib with high blockage ratio behind the air film hole, so that the upward deflected wall jet flow generated in the upstream area of the impact hole is mixed with the downward flow separated from the upper surface of the adjacent rib, and a smaller backflow area is generated behind the rib, thereby inhibiting the cross flow and enhancing the whole heat exchange of the structure. In addition, after the high-blockage-ratio fins are arranged on the wall surface of the impact target plate, the heat transfer performance of a low heat transfer area between impact jet flow areas on the impact target plate in the traditional impact cooling is improved, the flow resistance of the structure is reduced by parallel gaps among the fins, the pressure loss is reduced, and the air entraining amount is not increased while the heat exchange effect is enhanced.
In addition, because the fins strengthen the disturbance of cooling air flow, the convection heat exchange between fluid and solid in the double-layer wall is strengthened, and the total heat transfer quantity is correspondingly increased after the fins are arranged. Meanwhile, the fins weaken the development of transverse flow, so that more cooling air flows out of the air film holes to be mixed with high-temperature fuel gas, the air film cooling efficiency is improved, and finally the comprehensive cooling effect of the laminated plate structure is enhanced.
Drawings
FIG. 1 is a schematic view of the application of the cooling structure of the present invention to a turbine blade;
FIG. 2 is a schematic sectional view showing the structure of embodiment 1 of the present invention;
FIG. 3 is an enlarged cross-sectional view of a rib of a high plug ratio in example 1 of the present invention;
FIG. 4 is a schematic structural view of a half section of a rib structure with a high plug ratio in example 1 of the present invention;
FIG. 5 is a schematic view of the cooling principle of embodiment 1 of the present invention;
FIG. 6 is a schematic sectional view showing embodiment 2 of the present invention;
FIG. 7 is an enlarged cross-sectional view of a rib of a high plug ratio in example 2 of the present invention;
FIG. 8 is a schematic structural view of a half section of a rib structure with a high plug ratio in example 2 of the present invention;
FIG. 9 is a schematic view of the cooling principle of embodiment 2 of the present invention;
FIG. 10 is a schematic top view of the high blockage ratio fin structure of the present invention;
FIG. 11 is a graph showing the effect of the heat transfer enhancement factor of the present invention on the variation of the Reynolds number;
FIG. 12 is a graph showing the effect of the variation of the relative friction factor with Reynolds number in accordance with the present invention;
FIG. 13 is a graph showing the effect of the profile of the thermal performance of the present invention as a function of Reynolds number;
FIG. 14 is a graph showing the effect of the variation of the total cooling efficiency according to the Reynolds number.
In the figure, 1, impact hole, 2, impact orifice plate, 3, impact airflow cooling channel, 31, channel side wall, 4, high blockage ratio rib, 41, parallel slit, 42, parallel slit inlet, 43, parallel slit outlet, 5, air film hole, 6, air film orifice plate.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the utility model.
In order to achieve the above object, the present invention provides the following embodiments:
example 1: as shown in FIGS. 1-5 and 10, the cooling structure for the middle chord area of the turbine blade by using the high blockage ratio finned plate comprises a blade double-layer wall positioned in the middle chord of the blade, wherein the blade double-layer wall is formed by an air film orifice plate 6, an impact orifice plate 2 and an impact airflow cooling channel 3 between the air film orifice plate 6 and the impact orifice plate 2; the impact orifice plate 2 is an air inlet plate and is arranged on the cold air side of the turbine blade; the gas film pore plate 6 is a gas outlet plate, and the gas film pore plate 6 is arranged on the gas side of the turbine blade; the thickness of the impact orifice plate 2 and the thickness of the air film orifice plate 6 are both 0.5-3 d, and the width in the spreading direction is both 4-8 d.
The air film pore plate 6 is uniformly and equidistantly provided with air film pores 5, the impact pore plate 2 is uniformly and equidistantly provided with impact pores 1, and the air film pores 5 and the impact pores 1 are arranged in a staggered manner; the impact holes 1 and the air film holes 5 are respectively arranged on the impact hole plate 2 and the air film hole plate 6 in a direction perpendicular to the main airflow, the hole diameter d is 2-10 mm, and the relative distance between each two adjacent impact holes 1 and air film holes 5 along the airflow direction and the spreading direction is 4-8 d; the staggered interval between the impact holes 1 and the air film holes 5 is 2-4 d. The hole patterns of the impact hole 1 and the air film hole 5 are both cylindrical holes; the ratio of the height H of the impingement airflow cooling channel 3 to the aperture d is 0.5-3;
a high-blockage-ratio rib 4 is arranged on an air film pore plate 6 in the impingement airflow cooling channel 3 in an extending manner along the blade height direction of the turbine blade, and two ends of the high-blockage-ratio rib 4 are connected to channel side walls 31 of the impingement airflow cooling channel 3; the section of the high blockage ratio rib 4 is square, and the ratio of the height of the high blockage ratio rib 4 to the height H of the impinging stream cooling channel 3 is 0.2-0.5; the hole diameters of the impact holes 1 and the air film holes 5 are both the hole diameter d, the high-blockage-ratio fins 4 are positioned behind the air film holes 5 in the cooling air flow direction, and the distance between the high-blockage-ratio fins 4 and the air film holes 5 is 1-5 d;
the blade double-layer wall of the middle chord of the blade comprises a pressure surface and a suction surface. As shown in fig. 1, the portions marked with broken lines in the figure are the double walls of the blade for the pressure side and the suction side.
The specific structure example is as follows: as shown in fig. 10, the cooling structure provided by the present invention is applied to the chord region of a gas turbine blade of an aircraft engine, and the cooling structure is composed of a gas film hole 5, a gas film orifice plate 6, an impinging air flow cooling channel 3, a high blockage ratio rib 4, impingement holes 1 and impingement orifice plates 2, wherein the impingement orifice plates 2 are air inlet plates, the air inlet plates are close to the cold air side, the impingement holes 1 are uniformly arranged on the plates at equal intervals and perpendicular to the main flow direction, the impingement holes 1 are arranged in an array, the aperture d of the impingement holes 1 is 5mm, and as shown in fig. 10, the impingement holes 1 are arranged along the main flow direction P between the impingement holes 1fA relative distance P from the spanwise directionjAre all 6 d;the gas film pore plate 6 is a gas outlet plate, the gas film pore plate 6 is close to the gas side, gas film pores 5 which are perpendicular to the main flow direction and are arrayed are arranged on the plate, the pore diameter of each gas film pore 5 is also d, and the impact pores 1 are arranged along the main flow direction P between the impact poresfA relative distance P from the spanwise directionjAre all 6 d; and the air film holes 5 and the impact holes 1 are arranged in a staggered way at a distance PxThe thickness of the impact orifice plate 2 and the thickness of the air film orifice plate 6 are both 1.5 d; the impact distance, namely the ratio of the distance between the impact hole 1 and the impact target surface to the diameter d of the impact hole 1 is 1, the impact target surface refers to the inner wall surface of the air film pore plate 6, and the distance between the impact hole 1 and the impact target surface is the height H of the impact airflow cooling channel 3; the hole patterns of the impact holes 1 and the air film holes 5 are both cylindrical holes. The fins with high blocking ratio are arranged in a cooling channel formed by the air film hole plate and the impact hole plate, are oppositely positioned behind the air film hole 5 and are at a distance PrIs 1.5 d; the high blockage ratio ribs 4 are square ribs, the ratio of the rib height to the impingement channel height is 0.3, the slit angle alpha is 0 DEG and the 20 DEG penetration ratio beta is 0.05 and 0.4, wherein c is the height of the parallel slits 41 and e is the height of the high blockage ratio ribs 4.
As shown in FIG. 5, the cooling method of the turbine blade mid-chord region by the high blockage ratio finned plate cooling structure according to the embodiment 1 is as follows:
the cooling air flow carries out impact heat exchange on the inner wall surface of the air film pore plate 6 through the impact holes 1, the cooling air flow impacting the air film pore plate 6 is diffused to the periphery to form wall surface jet flow A, and then cross flow B is formed along the direction of the cold air flow; at this time, the high blockage ratio rib 4 plays a role of reinforcing disturbance on cooling airflow, the wall surface jet A1 deflected upwards generated in the upstream area of the impact hole 1 is mixed with the cooling airflow A2 flowing downwards and separated from the upper surface of the adjacent high blockage ratio rib 4, and a smaller backflow area A3 is generated behind the high blockage ratio rib 4, so that the development of cross flow B is inhibited, and the heat exchange is reinforced; meanwhile, the parallel slits 41 ensure that the heat exchange effect is enhanced, and the flow resistance of the cooling air flow is reduced and the pressure loss of the cooling air flow is reduced after the cooling air flow passes through the parallel slits 41;
and then, a part of cooling air flow enters the air film hole 5 to continue to carry out convective heat transfer, and is blown to the outer wall surface of the air film hole 5 to form an air film, so that the high-temperature gas is prevented from ablating the air film hole plate 6, and the other part of cooling air flow is discharged from an exhaust cavity at the tail edge of the blade.
Example 2: as shown in fig. 6 to 9, the parallel slits 41 are arranged obliquely with respect to the airflow direction, the inclination angle α is 0 to 30 °, and the penetration ratio β is 0.05 to 0.4, where c is the height of the parallel slits 41 and e is the height of the high blockage ratio rib 4.
As shown in FIG. 9, the cooling method of the turbine blade mid-chord cooling structure with the high blockage ratio rib-layer plate according to the embodiment 2 of the utility model is as follows:
the cooling airflow carries out impact heat exchange on the inner wall surface of the air film pore plate 6 through the impact holes 1, the cooling airflow impacting the air film pore plate 6 is diffused around to form wall surface jet flow A, and then cross flow B is formed along the direction of the flow direction of the cold air; at this time, the high blockage ratio rib 4 plays a role of reinforcing disturbance on the cooling air flow, the wall surface jet A1 deflected upwards generated in the upstream area of the impact hole 1 is mixed with the cooling air flow A2 flowing downwards and separated by the parallel slit 41 inclined relative to the air flow direction, and a smaller backflow area A3 is generated behind the high blockage ratio rib 4, so that the development of cross flow B is inhibited, and the heat exchange is reinforced; meanwhile, the parallel slits 41 ensure that the heat exchange effect is enhanced, and the flow resistance of cooling air flow is reduced and the pressure loss of the cooling air flow is reduced after the cooling air flow passes through the parallel slits 41;
and then, a part of cooling air flow enters the air film hole 5 to continuously carry out convection heat exchange, and is blown to the outer wall surface of the air film hole 5 to form an air film, so that the high-temperature gas is prevented from ablating the air film hole plate 6, and the other part of cooling air flow is discharged from an exhaust cavity at the tail edge of the blade.
As shown in fig. 11 to 14, the structural effect of the present invention is remarkable as follows:
as shown in FIG. 11, the larger the heat transfer enhancement factor, the stronger the heat exchange degree of the impact target surface, and this schematic diagram is mainly compared with the solid rib, and it is seen from the figure that the heat transfer enhancement factor of the perforated rib provided by the present invention is higher than that of the solid rib, which represents the heat exchange enhancement.
As shown in fig. 12, the relative friction factor represents the magnitude of the flow resistance of the perforated rib structure provided by the present invention, and it can be seen that the friction factor is smaller, i.e., represents a weakening of the flow resistance of the structure, compared to the solid rib.
As shown in fig. 13, the larger the integrated thermal performance, the higher the efficiency of the double-walled structure for improving heat exchange, and the integrated thermal performance represents the magnitude of the heat exchange strength of the structure of the present invention for increasing the heat exchange strength with the same pump work. This is shown primarily in comparison to solid ribs, and it can be seen that the present invention provides a perforated rib having a higher thermal profile than a solid rib, representing an increased efficiency.
As shown in fig. 14, the coupling effect of the external film cooling, the internal cooling and the heat conduction is considered in the comprehensive cooling efficiency, so that the cooling effect of the outer side (the side in contact with the high-temperature gas) of the film hole plate is reflected, and the larger the comprehensive cooling effect is, the better the cooling effect is. As seen from the figure, the comprehensive cooling efficiency of the seam crossing rib provided by the utility model is obviously improved compared with that of a solid rib, and represents that the comprehensive cooling efficiency is enhanced.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and should not be taken as limiting the scope of the present invention, which is intended to cover any modifications, equivalents, improvements, etc. within the spirit and scope of the present invention.
Claims (8)
1. A cooling structure of a rib-type laminate with a high blocking ratio for a middle chord region of a turbine blade is characterized by comprising a blade double-layer wall positioned at the middle chord of the blade, wherein the blade double-layer wall is composed of an air film pore plate (6), an impact pore plate (2) and an impact airflow cooling channel (3), the impact airflow cooling channel (3) is arranged between the air film pore plate (6) and the impact pore plate (2), air film holes (5) are uniformly arranged on the air film pore plate (6) at equal intervals, impact holes (1) are uniformly arranged on the impact pore plate (2) at equal intervals, and the air film holes (5) and the impact holes (1) are arranged in a staggered manner;
a high-blockage-ratio rib (4) extends along the blade height direction of the turbine blade on an air film pore plate (6) in the impingement airflow cooling channel (3), and two ends of the high-blockage-ratio rib (4) are connected to a channel side wall (31) of the impingement airflow cooling channel (3);
parallel slits (41) used for disturbing and reducing the flow resistance of cooling gas are formed in the high blockage ratio rib (4) along the direction of cooling gas flow, the cooling gas flow flows in from a parallel slit inlet (42) and flows out from a parallel slit outlet (43), and the parallel slits (41) are continuously or intermittently extended and arranged in the extending direction of the high blockage ratio rib (4); the upper and lower parallel slit surfaces of the parallel slit (41) are arranged in parallel, and the height of the parallel slit inlet (42) is the same as that of the parallel slit outlet (43);
the aperture of the impact hole (1) and the aperture of the air film hole (5) are both the aperture d, and along the direction of the cooling air flow, the high blocking ratio rib (4) is positioned behind the air film hole (5), and the distance between the high blocking ratio rib (4) and the air film hole (5) is 1-5 d.
2. The turbine blade mid-chord cooling structure with high blockage ratio fin-shaped laminates as claimed in claim 1, characterized in that the impingement orifice plate (2) is an air intake plate arranged on the cold air side of the turbine blade; the gas film pore plate (6) is a gas outlet plate, and the gas film pore plate (6) is arranged on the gas side of the turbine blade; the thickness of the impact pore plate (2) and the thickness of the air film pore plate (6) are both 0.5-3 d, and the width in the spreading direction is both 4-8 d.
3. The turbine blade mid-chord cooling structure with high blockage ratio fin-shaped laminate as claimed in claim 1, wherein the ratio of the height H of the impingement airflow cooling channel (3) to the aperture d is 0.5-3.
4. The turbine blade mid-chord zone fin-based laminate cooling structure for the turbine blade of claim 1, wherein the impingement holes (1) and the air film holes (5) are respectively arranged on the impingement hole plate (2) and the air film hole plate (6) in a direction perpendicular to the main air flow, the hole diameter d is 2-10 mm, and the relative distance between the adjacent impingement holes (1) and air film holes (5) in the air flow direction and the spreading direction is 4-8 d; the staggered interval of the impact holes (1) and the air film holes (5) is 2-4 d.
5. The turbine blade mid-chord cooling structure using high blockage ratio rib-plate as claimed in claim 4, wherein the impingement holes (1) and the film holes (5) are cylindrical holes.
6. The turbine blade mid-chord zone high blockage ratio fin deck cooling structure as claimed in claim 4, wherein the high blockage ratio fins (4) have a square cross-sectional shape, and the ratio of the height of the high blockage ratio fins (4) to the height H of the impingement airflow cooling channel (3) is 0.2 to 0.5.
7. The turbine blade mid-chord cooling structure for the high blockage ratio rib laminate as claimed in claim 4, wherein the parallel slits (41) are arranged obliquely with respect to the flow direction of the air flow, the inclination angle α is 0 to 30 °, and the penetration rate β ═ c/e is 0.05 to 0.4, wherein c is the height of the parallel slits (41) and e is the height of the high blockage ratio rib (4).
8. A turbine blade mid-chord cooling structure using high blockage ratio finned laminates as in any one of claims 1 to 7 wherein the blade double wall of the mid-chord of the blade comprises a pressure side and a suction side blade double wall.
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| CN202123293359.7U CN216642214U (en) | 2021-12-26 | 2021-12-26 | High-blockage-ratio finned laminate cooling structure for middle chord area of turbine blade |
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| CN202123293359.7U CN216642214U (en) | 2021-12-26 | 2021-12-26 | High-blockage-ratio finned laminate cooling structure for middle chord area of turbine blade |
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