CN114872909A - Aircraft type turbine blade cooling channel heat exchange structure - Google Patents
Aircraft type turbine blade cooling channel heat exchange structure Download PDFInfo
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- CN114872909A CN114872909A CN202210485291.2A CN202210485291A CN114872909A CN 114872909 A CN114872909 A CN 114872909A CN 202210485291 A CN202210485291 A CN 202210485291A CN 114872909 A CN114872909 A CN 114872909A
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- plane
- heat exchange
- inclined plane
- turbine blade
- cooling channel
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
- B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
- B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
- B64D33/10—Radiator arrangement
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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
Abstract
The invention provides an aircraft type turbine blade cooling channel heat exchange structure which comprises side heights, side planes, side inclined planes, a top plane, outer inclined planes, inner inclined planes, prisms and tetrahedrons, wherein the outer inclined planes and the inner inclined planes are obliquely arranged relative to a horizontal plane, the tops of the outer inclined planes and the inner inclined planes are connected through the top planes, the number of the side heights, the number of the side planes and the number of the side inclined planes are two, the side inclined planes, the side planes and the side heights are symmetrically and sequentially arranged on two sides of the top plane, the side inclined planes, the side planes and the side heights are connected with the outer inclined planes and the inner inclined planes, one end of each prism is connected with the middle part of the inner inclined plane and positioned on a midline of the inner inclined plane, and the tetrahedrons are connected with the other ends of the prisms. The embodiment of the invention can improve the heat exchange effect and improve the heat exchange coefficient by more than 90% compared with the prior art.
Description
Technical Field
The invention relates to the technical field of aero-engines, in particular to a heat exchange structure of a cooling channel of an airplane type turbine blade.
Background
In order to obtain higher thrust-weight ratio and thermal efficiency and continuously improve the temperature of a turbine inlet of a modern aviation gas turbine engine, the temperature of the turbine inlet is far higher than the melting point temperature of a blade material at present, a complex cooling technology is required to be adopted to keep the normal work of a turbine blade, the cooling technology of the turbine blade is divided into external cooling and internal cooling, the internal cooling is to strengthen the internal convection heat exchange of the turbine blade so as to lead cooling airflow to take away heat from the inner side of the blade, and the main mode comprises the measures of strengthening the heat exchange of a turbulent flow rib, carrying out impact cooling, reducing the temperature of cold air by adopting an indirect cooling method and the like.
Disclosure of Invention
In view of this, the embodiments of the present disclosure provide an aircraft turbine blade cooling channel heat exchange structure, so as to achieve the purpose of improving cooling efficiency.
The embodiment of the specification provides the following technical scheme: the utility model provides an aircraft type turbine blade cooling channel heat transfer structure, including the side height, the side plane, the side bevel, the apical plane, outer inclined plane, interior inclined plane, prism and tetrahedron, outer inclined plane and interior inclined plane set up for the horizontal plane slope, the apical plane is passed through at the top of outer inclined plane and interior inclined plane and is connected, the side height, side plane and side bevel are two, the bilateral symmetry of apical plane has set gradually the side bevel, side plane and side height, and the side bevel, side plane and side height all are connected with outer inclined plane and interior inclined plane, prismatic one end is connected with the middle part of interior inclined plane, and lie in the well bisector of interior inclined plane, the tetrahedron is connected with prismatic other end.
Further, the included angle between the outer inclined plane and the horizontal plane is alpha, the included angle between the inner inclined plane and the horizontal plane is beta, wherein alpha is 35-45 degrees, and beta is 30-35 degrees.
Further, the height of the heat exchange structure of the cooling channel of the airplane-type turbine blade is D, the length of the side height is L1, the length of the top plane is L8, the inclination angle of the side inclined plane is gamma, wherein L1 is more than or equal to 0.5D and less than or equal to 0.55D, L8 is more than or equal to 1.1D and less than or equal to 1.3D, and gamma is 20-25 degrees.
Furthermore, the height of the heat exchange structure of the cooling channel of the airplane-type turbine blade is D, the projection length of the outer inclined surface is L5, the projection length of the top plane is L6, and the projection length of the inner inclined surface is L7, wherein L5 is more than or equal to 1.1D and less than or equal to 1.3D, L6 is more than or equal to 0.5D and less than or equal to 0.6D, and L7 is more than or equal to 1.5D and less than or equal to 1.6D.
Furthermore, the height of the heat exchange structure of the cooling channel of the airplane-type turbine blade is D, the projection length of the heat exchange structure of the cooling channel of the airplane-type turbine blade is L2, the projection width is L4, and the projection length of the side plane is L3, wherein L2 is more than or equal to 4.9D and less than or equal to 5.1D, L3 is more than or equal to 1.3D and less than or equal to 1.4D, and L4 is more than or equal to 5.7D and less than or equal to 6.0D.
Furthermore, the height of the heat exchange structure of the cooling channel of the airplane-type turbine blade is D, the width of the prism is L9, and the width of the tetrahedron is L10, wherein L9 is more than or equal to 1.0D and less than or equal to 1.1D, and L10 is more than or equal to 2.1D and less than or equal to 2.2D.
Furthermore, the side height, the side plane, the side inclined plane, the top plane, the outer inclined plane and the inner inclined plane form a heat exchange unit, the heat exchange structure of the aircraft type turbine blade cooling channel comprises a plurality of heat exchange units, the heat exchange units are arranged at intervals, and the side heights of two adjacent heat exchange units in the same row are opposite in the direction perpendicular to the airflow direction.
Compared with the prior art, the beneficial effects that can be achieved by the at least one technical scheme adopted by the embodiment of the specification at least comprise: when cooling air flows through the tetrahedron, the airflow is lifted, so that the part of the lifted airflow forms a small vortex to exchange heat with the tetrahedron; when the airflow reaches the inner inclined surface, the airflow at the two sides is forced to flow towards the center of the turbulence rib because the two sides of the turbulence rib shrink towards the center, so that the disturbance between the airflow and the boundary layer of the turbulence rib is enhanced, and the heat exchange is enhanced; the air flow is lifted after exchanging heat with the turbulence ribs, vortex and cold air core flow mixing are formed, heat is exchanged, the temperature of the lifted air flow is reduced, and the lifted cold air enters the cold air core flow and rotates, so that part of the air flow which does not exchange heat with the turbulence ribs is rolled to the turbulence ribs to exchange heat with the turbulence ribs. The heat exchange process of the cold air and the turbulence ribs comprises heat exchange, temperature rise, mixing, temperature reduction and heat exchange. Because the air current with the heat transfer of vortex rib is the air current through the mixing cooling all the time, therefore the heat transfer is effectual, compares in rectangle heat transfer structure of this embodiment, and heat transfer coefficient promotes more than 90%.
Drawings
In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings needed to be used in the embodiments will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present application, and it is obvious for those skilled in the art to obtain other drawings based on these drawings without creative efforts.
FIG. 1 is a three-dimensional schematic of an embodiment of the present invention;
FIG. 2 is a cross-sectional view of an embodiment of the present invention;
FIG. 3 is a sectional view taken along line A-A of FIG. 2;
FIG. 4 is a front view of an embodiment of the present invention;
FIG. 5 is a top view of an embodiment of the present invention;
FIG. 6 is a bottom view of an embodiment of the present invention;
FIG. 7 is a schematic diagram of an arrangement of heat exchange units according to an embodiment of the present invention;
FIG. 8 is a graph of Knoop number as a function of Reynolds number.
Reference numbers in the figures: 1. side height; 2. a side plane; 3. a side bevel; 4. a top plane; 5. an outer bevel; 6. an inner bevel; 7. a prism; 8. a tetrahedron.
Detailed Description
The embodiments of the present application will be described in detail below with reference to the accompanying drawings.
It should be noted that the embodiments and features of the embodiments in the present application may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
As shown in fig. 1 to 7, an embodiment of the present invention provides an aircraft turbine blade cooling channel heat exchange structure, where the aircraft turbine blade cooling channel heat exchange structure includes a side height 1, a side plane 2, a side slope 3, a top plane 4, an outer slope 5, an inner slope 6, a prism 7, and a tetrahedron 8, the outer slope 5 and the inner slope 6 are arranged obliquely with respect to a horizontal plane, tops of the outer slope 5 and the inner slope 6 are connected through the top plane 4, the number of the side height 1, the side plane 2, and the side slope 3 are two, the side plane 2, and the side height 1 are symmetrically arranged on two sides of the top plane 4 in sequence, the side slope 3, the side plane 2, and the side height 1 are connected with the outer slope 5 and the inner slope 6, one end of the prism 7 is connected with a middle portion of the inner slope 6 and located on a bisector of the inner slope 6, and the tetrahedron 8 is connected with the other end of the prism 7.
When the cooling air flows through the tetrahedron 8, the airflow is lifted, so that the part of the lifted airflow forms a small vortex to exchange heat with the tetrahedron 8; when the airflow reaches the inner inclined plane 6, the airflow at the two sides is forced to flow towards the center of the turbulence rib because the two sides of the turbulence rib shrink towards the center, so that the disturbance between the airflow and the boundary layer of the turbulence rib is enhanced, and the heat exchange is enhanced; the air flow is lifted after exchanging heat with the turbulence ribs, vortex and cold air core flow mixing are formed, heat is exchanged, the temperature of the lifted air flow is reduced, and the lifted cold air enters the cold air core flow and rotates, so that part of the air flow which does not exchange heat with the turbulence ribs is rolled to the turbulence ribs to exchange heat with the turbulence ribs. The heat exchange process of the cold air and the turbulence ribs comprises heat exchange, temperature rise, mixing, temperature reduction and heat exchange. Because the air current of the heat transfer with the vortex rib is the air current through the mixing cooling all the time, therefore the heat transfer effect is very good. This embodiment is compared in rectangle heat transfer structure, and the heat transfer coefficient promotes 90%.
In this embodiment, the inner inclined plane 6 is formed by connecting two symmetrical inclined planes, the joint of the two inclined planes is a middle dividing line of the inner inclined plane 6, and the middle dividing line of the inner inclined plane 6 is of a concave structure. The outer inclined plane 5 is formed by connecting two symmetrical inclined planes, the joint of the two inclined planes is a middle parting line of the outer inclined plane 5, the middle parting line of the outer inclined plane 5 corresponds to the middle parting line of the inner inclined plane 6, and the middle parting line of the outer inclined plane 5 is in an outward convex structure.
The side height 1, the side plane 2, the side inclined plane 3 and the top plane 4 are sequentially connected and located between the outer inclined plane 5 and the inner inclined plane 6, and the side height 1, the side plane 2, the side inclined plane 3 and the top plane 4 are used for connecting the outer inclined plane 5 and the inner inclined plane 6.
The prism 7 is provided with two symmetrically arranged inclined planes, and the joint of the two inclined planes of the prism 7 is in an outer convex shape and corresponds to the middle line of the inner inclined plane 6. The tetrahedron 8 is of a frustum structure, and the top view of the tetrahedron 8 has four symmetrically arranged triangular faces, wherein the symmetrical center line is the plane where the bisector of the inner inclined plane 6 is located. The triangular surface is four inclined planes of a tetrahedron 8, and the vertexes of the four inclined planes are located at the ends of the two inclined slopes of the prism 7.
As shown in fig. 3, the included angle between the outer inclined surface 5 and the horizontal plane is α, the included angle between the inner inclined surface 6 and the horizontal plane is β, wherein α is 35 ° to 45 °, and β is 30 ° to 35 °; the included angles alpha and beta between the outer inclined surface 5 and the horizontal plane enable the airflow to be gently lifted, sudden expansion is avoided, and meanwhile, the heat exchange area is increased; the air flow is gently reduced under the action of the included angle between the inner inclined plane 6 and the horizontal plane, sudden shrinkage is avoided, and meanwhile, the heat exchange area is increased.
The height of the heat exchange structure of the cooling channel of the airplane turbine blade is D, the length of the side height 1 is L1, the length of the top plane 4 is L8, the inclination angle of the side inclined plane 3 is gamma, wherein L1 is more than or equal to 0.5D and less than or equal to 0.55D, L8 is more than or equal to 1.1D and less than or equal to 1.3D, and gamma is 20-25 degrees. The length L1 of the side height 1 is about half of the height D of the cooling channel heat exchange structure of the airplane turbine blade, and the function of the side height is to enable airflow to be closer to a lower plane when the airflow flows on two sides; the length L8 of the top plane 4 is slightly larger than D, so that the heat exchange area of the top is increased; the inclination angle γ of the side bevel 3 has the effect of making a smooth transition between the side plane 2 and the top plane 4.
The height of the heat exchange structure of the cooling channel of the airplane turbine blade is D, the projection length of the outer inclined surface 5 is L5, the projection length of the top plane 4 is L6, and the projection length of the inner inclined surface 6 is L7, wherein L5 is more than or equal to 1.1D and less than or equal to 1.3D, L6 is more than or equal to 0.5D and less than or equal to 0.6D, and L7 is more than or equal to 1.5D and less than or equal to 1.6D. The projection lengths L5 and L7 of the outer inclined surface 5 and the inner inclined surface 6 are slightly longer than D, so that the air flow has more heat exchange time, and the projection length L6 of the top plane 4 is about half of D, so that the top air flow can also exchange heat with the top plane 4.
The projection length of the heat exchange structure of the cooling channel of the airplane turbine blade is L2, the projection width is L4, and the projection length of the side plane 2 is L3, wherein L2 is more than or equal to 4.9D and less than or equal to 5.1D, L3 is more than or equal to 1.3D and less than or equal to 1.4D, and L4 is more than or equal to 5.7D and less than or equal to 6.0D. The projection length L2 and the projection width L4 of the heat exchange structure are far larger than D, so that the heat exchange area can be increased, and the projection length L3 of the side plane 2 can stir airflow to enable the airflow to generate vortices.
The width of the prism 7 is L9, the width of the tetrahedron 8 is L10, L9 is more than or equal to 1.0D and less than or equal to 1.1D, and L10 is more than or equal to 2.1D and less than or equal to 2.2D. The width L9 of prism 7 increases the heat exchange area while agitating the airflow; the width L10 of the tetrahedron 8 increases the heat exchange area.
As shown in fig. 7, the side height 1, the side plane 2, the side inclined plane 3, the top plane 4, the outer inclined plane 5 and the inner inclined plane 6 form a heat exchange unit, the heat exchange structure of the cooling channel of the aircraft turbine blade comprises a plurality of heat exchange units, the plurality of heat exchange units are arranged at intervals, and the side heights 1 of two adjacent heat exchange units are opposite. Set up a plurality of heat transfer units and can maximize heat exchange efficiency, simultaneously according to different heat transfer demands, the heat transfer unit of different quantity can be selected to this embodiment to satisfy different operating mode conditions.
The applicant has compared the heat exchange effect of rectangle heat transfer structure, W type heat transfer structure and this embodiment (aircraft shape) in numerical calculation, and this embodiment compares in rectangle heat transfer structure, and heat transfer coefficient promotes 90%, and than the W type heat transfer structure of high performance, and heat transfer coefficient promotes 30% to outer wall temperature distribution is more even. Meanwhile, the Knudell numbers of the embodiment are the highest under different Reynolds numbers, and the increase of the Knudell numbers is more obvious along with the increase of the Reynolds numbers, as shown in FIG. 8, a square frame in the figure is a rectangular heat exchange structure, a diamond figure is a W-shaped heat exchange structure, and a round figure is the embodiment of the invention.
The above description is only exemplary of the invention and should not be taken as limiting the scope of the invention, so that the invention is intended to cover all modifications and equivalents of the embodiments described herein. In addition, the technical features, the technical schemes and the technical schemes can be freely combined and used.
Claims (7)
1. An aircraft type turbine blade cooling channel heat exchange structure is characterized by comprising a lateral height (1), a lateral plane (2), a lateral inclined plane (3), a top plane (4), an outer inclined plane (5), an inner inclined plane (6), prisms (7) and tetrahedrons (8), wherein the outer inclined plane (5) and the inner inclined plane (6) are obliquely arranged relative to a horizontal plane, the tops of the outer inclined plane (5) and the inner inclined plane (6) are connected through the top plane (4), the lateral height (1), the lateral plane (2) and the lateral inclined plane (3) are respectively two, the lateral inclined plane (3), the lateral plane (2) and the lateral height (1) are symmetrically and sequentially arranged on two sides of the top plane (4), the lateral inclined plane (3), the lateral plane (2) and the lateral height (1) are respectively connected with the outer inclined plane (5) and the inner inclined plane (6), one end of each prism (7) is connected with the middle part of the inner inclined plane (6) and is positioned on a bisector of the inner inclined plane (6), the tetrahedron (8) is connected with the other end of the prism (7).
2. The aircraft turbine blade cooling channel heat exchange structure of claim 1, wherein the angle between the outer bevel (5) and the horizontal plane is α, and the angle between the inner bevel (6) and the horizontal plane is β, wherein α is 35 ° to 45 ° and β is 30 ° to 35 °.
3. The aircraft turbine blade cooling channel heat exchange structure of claim 1, wherein the height of the aircraft turbine blade cooling channel heat exchange structure is D, the length of the side height (1) is L1, the length of the top plane (4) is L8, and the inclination angle of the side slope (3) is γ, wherein 0.5D ≦ L1 ≦ 0.55D, 1.1D ≦ L8 ≦ 1.3D, and γ is 20 ° to 25 °.
4. The aircraft turbine blade cooling channel heat exchange structure of claim 1, wherein the height of the aircraft turbine blade cooling channel heat exchange structure is D, the projection length of the outer inclined plane (5) is L5, the projection length of the top plane (4) is L6, and the projection length of the inner inclined plane (6) is L7, wherein 1.1D ≦ L5 ≦ 1.3D, 0.5D ≦ L6 ≦ 0.6D, and 1.5D ≦ L7 ≦ 1.6D.
5. The aircraft type turbine blade cooling channel heat exchange structure of claim 1, wherein the height of the aircraft type turbine blade cooling channel heat exchange structure is D, the projected length of the aircraft type turbine blade cooling channel heat exchange structure is L2, the projected width is L4, and the projected length of the side plane 2 is L3, wherein L2 is 4.9D or more and 5.1D or less, L3 is 1.3D or more and 1.4D or less, and L4 is 5.7D or more and 6.0D or less.
6. The aircraft turbine blade cooling channel heat exchanging structure of claim 1, wherein the height of the aircraft turbine blade cooling channel heat exchanging structure is D, the width of the prism (7) is L9, and the width of the tetrahedron (8) is L10, wherein L9 is 1.0D or more and L9 is 1.1D or less, and L10 is 2.2D or more and 2.1D or more.
7. The aircraft type turbine blade cooling channel heat exchange structure according to claim 1 is characterized in that the side height (1), the side plane (2), the side inclined plane (3), the top plane (4), the outer inclined plane (5) and the inner inclined plane (6) form one heat exchange unit, the aircraft type turbine blade cooling channel heat exchange structure comprises a plurality of heat exchange units, the heat exchange units are arranged at intervals, and the side heights (1) of two adjacent heat exchange units in the same row are opposite in a direction perpendicular to the airflow direction.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202210485291.2A CN114872909B (en) | 2022-05-06 | 2022-05-06 | Aircraft type turbine blade cooling channel heat exchange structure |
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| CN202210485291.2A CN114872909B (en) | 2022-05-06 | 2022-05-06 | Aircraft type turbine blade cooling channel heat exchange structure |
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| CN114872909B CN114872909B (en) | 2023-03-24 |
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