CN111022127B - Turbine blade trailing edge curved exhaust split structure - Google Patents
Turbine blade trailing edge curved exhaust split structure Download PDFInfo
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- CN111022127B CN111022127B CN201911197684.8A CN201911197684A CN111022127B CN 111022127 B CN111022127 B CN 111022127B CN 201911197684 A CN201911197684 A CN 201911197684A CN 111022127 B CN111022127 B CN 111022127B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
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Abstract
The invention belongs to the technical field of aircraft engine turbine cooling, and relates to a curved exhaust split structure of a turbine blade trailing edge. The curved exhaust split structure comprises a hollow turbine blade, an inner cavity cold air channel, a tail edge exhaust split channel and a tail edge split partition rib; the hollow turbine blade is internally provided with an inner cavity cold air channel for low-temperature cooling gas to flow inside the blade to cool the blade. The tail edges of the hollow turbine blades are provided with tail edge slit partition ribs which are arranged side by side, and tail edge exhaust slit channels are formed among the tail edge slit partition ribs which are arranged side by side so as to exhaust cooling air out of the blades. The invention designs the tail edge cleft seam of the blade into the inclined curve type exhaust, reduces the turning angle of the cooling air in the cleft seam, ensures that the turning process is continuous and mild, thereby reducing the flow resistance and loss of the cooling air in the cavity of the blade and reducing the flow resistance by about 20 percent.
Description
Technical Field
The invention belongs to the technical field of aircraft engine turbine cooling, and relates to a curved exhaust split structure of a turbine blade trailing edge.
Background
Increasing the turbine front gas temperature can greatly improve the efficiency of aircraft engines and gas turbines, but the current turbine front gas temperature is far beyond the limit that the materials used can bear, so that the development of more effective turbine blade cooling technology is urgent. At present, the turbine blade is generally designed in a hollow mode, heat is taken away through enhanced convection heat exchange of cooling air in the turbine blade, and an air film is formed to cover and isolate fuel gas for heating when the turbine blade is discharged, so that the turbine blade is a main solution for the cooling problem of the turbine blade, and the turbine blade is mainly focused and pursued by the requirements of larger internal heat exchange area, smaller cold air flow resistance, higher heat exchange efficiency, larger air film coverage area, smaller structural strength damage and the like.
The tail edge area of the turbine blade is heated by combustion gas on the two sides of the basin side and the back side of the blade, and is structurally thin and difficult to form a hollow cooling structure, so that the tail edge area is an area difficult to cool in the blade, is an area with high wall surface temperature and easy ablation in work, and is a difficult problem to be mainly solved in the blade cooling design. At present, a half-open horizontal exhaust split structure is usually adopted for cooling the tail edge of the blade, the structure can convert cold air flowing in a cooling channel in the blade along the radial direction into cold air flowing along the chord direction, after strengthened convection cooling is formed on the wall surface of the channel and the rib structure, the cold air is exhausted from a narrow gap (called a split gap) at the edge of the basin side of the blade, and an air film is formed on the part of the tail edge to cover and isolate heating of fuel gas, and the typical structure is shown in figure 1 and is basically characterized in that the split gap horizontally exhausts the air. The tail edge slot-splitting cooling structure has large flow resistance and low cooling effect, and also has certain damage to the structural strength of the blade.
Disclosure of Invention
Aiming at the defects of the existing horizontal exhaust tail edge slot cooling technology, the curved exhaust slot structure of the turbine blade tail edge is provided, and the curved exhaust slot structure of the turbine blade tail edge is designed to be inclined for exhaust, so that the turning angle of cooling air can be effectively reduced, the smoothness of cold air flow is improved, the flow resistance is reduced, the air film coverage width is increased, the heat exchange effect is enhanced, the load resistance of the structure is improved, and the blade casting manufacturability is improved.
The technical scheme of the invention is as follows:
a turbine blade trailing edge curved type exhaust split structure comprises a hollow turbine blade, an inner cavity cold air channel, a trailing edge exhaust split channel and a trailing edge split partition rib;
the hollow turbine blade is internally provided with an inner cavity cold air channel for low-temperature cooling gas to flow inside the blade to cool the blade. The tail edges of the hollow turbine blades are provided with tail edge slit partition ribs which are arranged side by side, and tail edge exhaust slit channels are formed among the tail edge slit partition ribs which are arranged side by side so as to exhaust cooling air out of the blades and simultaneously carry out air film covering cooling on the tail edges of the blades. The structure of the tail edge slot partition rib can increase the heat exchange area in the blade, and guide the cooling air in the inner cavity of the blade to make the flowing direction of the cooling air turn.
The structural shape of the tail edge slot partition rib is controlled by a partition rib central line, the partition rib central line is a circular arc or spline curve, and the corresponding tail edge slot partition rib forms a circular arc or spline curve shape. The width of the tail edge slit partition rib is symmetrically distributed along the center line of the partition rib. Included angles between tangential directions of a trailing edge exhaust splitting seam central line at a cold air inlet end and an outlet end of the hollow turbine blade and a horizontal plane are an incident angle A1 and an emergent angle A2 respectively, and the included angle is A1> A2, and the included angle between a flow direction of cold air after entering the trailing edge splitting seam and a flow direction before entering the trailing edge splitting seam is less than 90 degrees.
Further, the incident angle a1 can be 15-45 °, the emergent angle a2 can be 0-30 °, and the cold air turning angle a at this time is.
In the original structure, as shown in fig. 1, the center line of the partition rib is a horizontal straight line, the inlet/outlet angles & lt a1 and & lt a2 of the cold air in the tail edge splitting seam are both 0 °, at the moment, the turning angle & lt a of the cold air is about 90 °, the turning angle is too large, the flow loss is large, the air film coverage area is small, and the strength damage is large. In the scheme of the invention, after the center line of the partition rib is changed into an inclined curve, the inlet/outlet angles A1 and A2 of the cold air in the tail edge splitting seam are acute angles, the turning angle of the cold air is also changed into an acute angle correspondingly, and the cold air flows in the curve type channel, so that the turning process is more continuous and mild, the flow is smoother, the flow resistance and loss are reduced, the air film coverage area is increased, and the load resistance of the tail edge hollow structure is improved.
The principle of the invention is as follows:
the inclined curve type structure of the invention reduces the flow resistance and loss of the cold air in the inner cavity of the blade:
compared with the original horizontal exhaust tail edge slot structure, the invention has the beneficial effects that the cold air flow resistance and loss are reduced. For the horizontal exhaust tail edge slot structure, the cooling gas needs to complete 90-degree direction turning at high speed in a narrow space, and such flow can form approximate step flow on the leeward side of the end part of the partition rib to generate low-speed vortex, as shown in fig. 3, the vortex flow not only generates energy dissipation due to the strong friction thereof, but also extrudes the main flow to force the main flow to generate additional direction turning and energy loss. The driving of the cold air flow needs to extract energy from the whole engine, so the high resistance flow can increase the power consumption of the whole engine, thereby reducing the efficiency. When the partition ribs of the split slot are changed into an inclined curve structure from the horizontal state, the turning angle of the cooling air in the split slot is changed from an approximate right angle to an acute angle, and the numerical value is reduced by more than 40%. The cold air flows in the curved channel, the turning process of the cold air is more continuous and mild, particularly, no obvious step is formed on the leeward side of the partition rib, and vortex cannot be formed, so that the flow is smoother, and the flow resistance and loss are reduced under the same flow rate, and the efficiency of the whole engine is improved.
2, the inclined curve type structure of the invention improves the gas film covering effect of the tail edge area of the blade:
after the cooling gas is discharged through the tail edge cleft seam, a gas film covering can be formed on the tail edge structure of the blade, and the heating of the gas on the basin side of the blade is isolated. For a horizontal exhaust tail edge split seam, the cold air outflow direction is approximately parallel to the gas, the cold air can not be radially deflected under the entrainment of the gas, and therefore, for a single split seam, the gas film coverage width is approximately the same as the actual width of the split seam. And the rib area between two adjacent clefts can hardly be covered by the air film, and the area which can not be covered by the air film is called as an air film covering dead area, wherein the cooling effect is poor, and high-temperature ablation is easily caused. For the inclined curve type exhaust tail edge cleavage slot, the gas film outflow direction and the gas flowing direction form a certain included angle, which can be approximately considered as ^ A2, because of the wrapping effect of the gas on the gas film outflow, the cold air is deflected in the flowing direction and gradually becomes parallel to the gas flowing direction, thereby realizing the covering of partial partition rib areas, and greatly increasing the covering width of the actual gas film outflow relative to the cleavage slot width, as shown in fig. 4. Even can make the original air film between two adjacent cleft seams cover "dead zone" and be eliminated completely through optimal design, form the air film and to the whole covers of blade trailing edge, reduce the temperature level of blade under the condition of not increasing the air conditioning quantity to realize the improvement of engine security under the prerequisite of guaranteeing economic nature.
The inclined curve type structure improves the load resistance of the hollow structure at the tail edge of the blade:
the turbine blades are subjected in operation mainly to the following loads: centrifugal loads caused by high-speed rotation, aerodynamic loads exerted by the gas flow, vibratory loads due to vibrations, which exert a tendency to deform in tension, torsion and bending on the blade base body and to generate corresponding stresses, and thermal stresses due to thermal expansion non-uniformities. These stresses couple together and act on the component alternately for long periods of time, and after exceeding the limits that the material can withstand, failure can occur. The blade design requires the use of a minimum of materials optimized to withstand these loads, avoiding the presence of high stress areas and damage to the blade. The tail edge crack structure is a vulnerable area with higher stress level in the turbine blade, the vulnerable area is firstly positioned at the thinnest part in the blade profile, and the hollow structure of the crack greatly weakens the strength, so that stress concentration can be generated at the opening of the crack. As shown in fig. 5(b), the stress level of the tail edge split structure shows a periodic law along the leaf height direction under the action of the radial tensile load, and shows a peak of the stress at the split opening and a trough at the partition rib. For a horizontal exhaust tail edge split, the periodicity is more pronounced and the peak value is higher because of the high degree of hollowing of the material at the tail edge, lack of effective support and reinforcement at the cross-sectional location shown in fig. 5 (a). When the inclined curve type exhaust tail edge slit structure is adopted, as shown in fig. 5(c), the partition rib structure can be connected with the two sides of the basin back of the blade at any section position, so that the tail edge structure is strengthened, the stress level is improved, the load resistance of the structure is improved, and the safety and the reliability of the whole machine are improved. As can be seen from the comparison of the stress distribution along the blade height of the trailing edge shown in FIG. 5(b), the peak stress of the oblique-curve exhaust trailing edge split structure is significantly less than that of the horizontal exhaust mode.
4, the inclined curve type structure improves the blade casting manufacturability:
the turbine blade is a part with higher manufacturing cost, usually adopts zero-allowance precision casting, has lower qualification rate, and particularly needs to adopt a directional solidification process for a monocrystalline turbine blade (the molten metal is crystallized into a crystal grain during solidification, and has better mechanical property at high temperature and gas corrosion resistance compared with a polycrystalline blade), namely the molten metal is gradually cooled to a solidification state from bottom to top. Since the volume of the metal is reduced from liquid to solid, the liquid metal must be ensured to have better fluidity in the casting shell during the structural design and the corresponding manufacturing process design of the blade, and the liquid metal can be timely supplemented to the space generated after solidification shrinkage, which is called feeding. If the feeding path of the molten metal is blocked and the feeding is insufficient, dense fine holes are generated when the molten metal in the corresponding region is solidified, which is called a loosening phenomenon. The looseness can cause the mechanical property of the material and the load resistance of the blade to be greatly reduced, belongs to a serious quality problem and must be scrapped. For the horizontal exhaust tail edge slot structure, as shown in the left side of fig. 6, because the liquid-solid interface of metal can take a slightly downward concave shape because the temperature of the outer side of the blade is lower than that of the inner side, a part of feeding paths of the rib structure can be blocked, so that the horizontal rib structure is easy to cause a loosening problem, and the blade has poor casting manufacturability. For the oblique curved exhaust tail edge slot splitting structure, as shown in the right side of fig. 6, the rib partition structure forms a certain included angle with the liquid-solid boundary, and the oblique rib partition structure just forms a molten metal feeding channel, so that the occurrence of looseness is avoided, and the casting manufacturability of the blade is improved.
The invention has the beneficial effects that:
the turbine blade curved exhaust tail edge slot cooling structure provided by the invention reduces the turning angle of cooling air in the slot by designing the blade tail edge slot into inclined curved exhaust, so that the turning process is continuous and moderate, the flow resistance and loss of the cooling air in the blade cavity are reduced, and the flow resistance can be reduced by about 20%. The gas film outflow direction of the inclined curve type exhaust and the gas flow direction form a certain included angle, so that the gas has a wrapping and clamping effect on the gas film outflow to improve the gas film covering effect of the tail edge area of the blade, and the heat exchange can be enhanced by about 11%. Through designing the partition ribs into the inclined curve type structure to strengthen the hollow structure of the tail edge of the blade, compared with a horizontal exhaust tail edge split cooling structure, the load resistance of the structure of the tail edge of the blade can be improved by about 21%. In addition, the inclined rib structures can form molten metal feeding channels, so that the blade casting manufacturability is improved, and the casting qualified rate can be improved by about 15%.
Drawings
FIG. 1(a) is a view showing a horizontal exhaust cleft at the trailing edge of a conventional turbine blade.
FIG. 1(b) is a C-C sectional view of a horizontal exhaust cleft structure of the tail edge of the prior turbine blade.
FIG. 1(c) is a partial enlarged view of a prior art turbine blade trailing edge horizontal exhaust slot structure.
FIG. 2(a) is a view showing a curved exhaust cleft at the trailing edge of a turbine blade.
FIG. 2(b) is a partial enlarged view of a curved exhaust slot at the trailing edge of a turbine blade.
FIG. 3 is a comparison diagram of cooling gas flow conditions in two tail edge cleavage slit structures.
FIG. 4 is a comparison graph of the gas film covering effect of two tail edge slit structures.
FIG. 5(a) is a schematic sectional view of a blade profile of a conventional turbine blade trailing edge horizontal exhaust slot structure.
FIG. 5(b) is a graph showing the comparison of stress levels of two types of tail edge split structures.
FIG. 5(c) is a schematic view of the blade profile cross-sectional shape of the curved exhaust slot structure at the trailing edge of the turbine blade.
FIG. 6 is a comparative diagram of the directional solidification casting process of two tail edge slot splitting structures.
In the figure: 1. a hollow turbine blade; 2. an inner cavity cold air channel; 3. a trailing edge exhaust slit channel; 4. the tail edge splits the seam and separates the rib; 5. the center line of the partition rib; 6. the tail edge is exhausted and splits the seam central line; 7. incident angle a 1; 8. an emergence angle < A2; 9. cold air turning angle A; 10. a cold air passage partition wall; 11. a cold air film coverage area; 12. the gas film coverage width; 13. a high stress area at the split seam opening; 14. and low stress areas at the seam splitting partition ribs.
Detailed Description
In order that the present invention may be more readily and clearly understood, a more particular description of the invention briefly described above will be rendered by reference to specific embodiments that are illustrated in the appended drawings.
Example 1:
please refer to fig. 2. A turbine blade trailing edge curved type exhaust split structure comprises a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust split channel 3 and a trailing edge split partition rib 4;
the hollow turbine blade 1 is internally provided with an inner cavity cold air channel 2 for low-temperature cooling gas to flow inside the blade to cool the blade. The tail edge of the hollow turbine blade 1 is provided with tail edge slit partition ribs 4 which are arranged side by side, and a tail edge exhaust slit channel 3 is formed between the tail edge slit partition ribs 4 which are arranged side by side so as to discharge cooling air out of the blade and simultaneously carry out air film covering cooling on the tail edge of the blade. The structure of the tail edge slot-splitting partition rib 4 can increase the heat exchange area in the blade, and guide the cooling air in the inner cavity of the blade to make the flowing direction of the cooling air turn.
The structural shape of the tail edge slot partition rib 4 is controlled by a partition rib central line 5, the partition rib central line 5 is an arc or a spline curve, and the corresponding tail edge slot partition rib 4 forms an arc or spline curve. The width of the tail edge slit partition rib 4 is symmetrically distributed along the center line 5 of the partition rib. Included angles between the tangential directions of the trailing edge exhaust splitting center line 6 at the cold air inlet end and the outlet end of the hollow turbine blade 1 and the horizontal plane are an incident angle A1 and an emergent angle A2, and the angle A1> angle A2. Typical values may be ═ a1 ═ 45 ° and ═ a2 ═ 30 °, at which time the cold gas turning angle ═ a is about 45 °.
Example 2:
please refer to fig. 2. A turbine blade trailing edge curved type exhaust split structure comprises a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust split channel 3 and a trailing edge split partition rib 4;
the structural shape of the tail edge slot partition rib 4 is controlled by a partition rib central line 5, the partition rib central line 5 is a circular arc or a spline curve, and the corresponding tail edge slot partition rib 4 forms a circular arc or a spline curve. The width of the tail edge slit partition rib 4 is symmetrically distributed along the center line 5 of the partition rib. Included angles between the tangential directions of the trailing edge exhaust splitting center line 6 at the cold air inlet end and the outlet end of the hollow turbine blade 1 and the horizontal plane are an incident angle A1 and an emergent angle A2, and the angle A1> angle A2. Typical values may be ═ a1 ═ 15 ° and ═ a2 ═ 0 °, at which time the cold gas turning angle ═ a is about 75 °.
Example 3:
please refer to fig. 2. A turbine blade trailing edge curved type exhaust split structure comprises a hollow turbine blade 1, an inner cavity cold air channel 2, a trailing edge exhaust split channel 3 and a trailing edge split partition rib 4;
the structural shape of the tail edge slot partition rib 4 is controlled by a partition rib central line 5, the partition rib central line 5 is a circular arc or a spline curve, and the corresponding tail edge slot partition rib 4 forms a circular arc or a spline curve. The width of the tail edge slit partition rib 4 is symmetrically distributed along the center line 5 of the partition rib. Included angles between the tangential directions of the trailing edge exhaust splitting center line 6 at the cold air inlet end and the outlet end of the hollow turbine blade 1 and the horizontal plane are an incident angle A1 and an emergent angle A2, and the angle A1> angle A2. Typical values may be ═ a1 ═ 25 ° and ═ a2 ═ 15 °, at which time the cold gas turning angle ═ a is about 65 °.
Claims (1)
1. A turbine blade trailing edge curved type exhaust split structure is characterized by comprising a hollow turbine blade (1), an inner cavity cold air channel (2), a trailing edge exhaust split channel (3) and a trailing edge split partition rib (4);
an inner cavity cold air channel (2) is arranged inside the hollow turbine blade (1), tail edge split joint partition ribs (4) which are arranged side by side are arranged at the tail edge of the hollow turbine blade (1), a tail edge exhaust split joint channel (3) is formed between the tail edge split joint partition ribs (4) which are arranged side by side, the structural shape of the tail edge split joint partition ribs (4) is controlled by a partition rib central line (5), the partition rib central line (5) is a circular arc or spline curve, and a circular arc or spline curve shape is formed corresponding to the tail edge split joint partition ribs (4); the width of the tail edge splitting slit partition rib (4) is symmetrically distributed along a partition rib central line (5), the width of the tail edge splitting slit partition rib (4) is gradually changed from narrow to wide along the cold air flowing direction, the tangential directions of the tail edge exhaust splitting slit central line (6) at the cold air inlet end and the outlet end of the hollow turbine blade (1) and the horizontal plane included angle are an incident angle & lt A1 and an emergent angle & lt A2 respectively, and & lt A1 & gt & lt A2, the incident angle & lt A1 is 45 degrees, the emergent angle & lt A2 is 30 degrees, and the cold air turning angle & lt A is 45 degrees.
Priority Applications (2)
| Application Number | Priority Date | Filing Date | Title |
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| CN201911197684.8A CN111022127B (en) | 2019-11-29 | 2019-11-29 | Turbine blade trailing edge curved exhaust split structure |
| PCT/CN2020/127687 WO2021104002A1 (en) | 2019-11-29 | 2020-11-10 | Curvilinear exhaust slit structure for trailing edge of turbine blade |
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| CN201911197684.8A CN111022127B (en) | 2019-11-29 | 2019-11-29 | Turbine blade trailing edge curved exhaust split structure |
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| CN111022127B true CN111022127B (en) | 2021-12-03 |
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| CN111022127B (en) * | 2019-11-29 | 2021-12-03 | 大连理工大学 | Turbine blade trailing edge curved exhaust split structure |
| CN112177683B (en) * | 2020-09-29 | 2021-08-20 | 大连理工大学 | Candida type turbine blade tail edge crack cooling structure |
| CN112177682B (en) * | 2020-09-29 | 2021-08-10 | 大连理工大学 | Turbine blade trailing edge crack cooling structure adopting wavy partition ribs |
| CN114526125B (en) * | 2022-04-24 | 2022-07-26 | 中国航发四川燃气涡轮研究院 | Cooling unit with rotary cavity for bag and turbine blade structure |
| CN115203833B (en) * | 2022-05-29 | 2023-07-07 | 中国船舶重工集团公司第七0三研究所 | Air-cooled turbine movable blade modeling method for suction side exhaust |
| CN115169022B (en) * | 2022-05-29 | 2023-04-07 | 中国船舶重工集团公司第七0三研究所 | Method for molding air-cooled turbine movable blade exhausted from pressure side |
| CN114991878B (en) * | 2022-05-30 | 2023-07-07 | 哈尔滨工业大学 | Turbine pressure side half split joint cooling seal beard tail edge blade and forming method |
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Also Published As
| Publication number | Publication date |
|---|---|
| CN111022127A (en) | 2020-04-17 |
| WO2021104002A1 (en) | 2021-06-03 |
| WO2021104002A9 (en) | 2021-07-08 |
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