CN113513370A - Low-pressure turbine boundary layer forced transition method based on macro pore structure - Google Patents
Low-pressure turbine boundary layer forced transition method based on macro pore structure Download PDFInfo
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- CN113513370A CN113513370A CN202110986987.9A CN202110986987A CN113513370A CN 113513370 A CN113513370 A CN 113513370A CN 202110986987 A CN202110986987 A CN 202110986987A CN 113513370 A CN113513370 A CN 113513370A
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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
- F01D5/141—Shape, i.e. outer, aerodynamic form
- F01D5/145—Means for influencing boundary layers or secondary circulations
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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
- F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
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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
- F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
- F01D5/282—Selecting composite materials, e.g. blades with reinforcing filaments
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Abstract
A low-pressure turbine boundary layer forced transition method based on a macro pore structure comprises the following steps of 1) selecting parameters of a prefabricated body: the prefabricated body adopts an integral design, and the blade body length of the low-pressure turbine blade is increased by 0.3-0.6 percent relative to the blade body of the low-pressure turbine blade prepared from the high-temperature alloy; 2) the design of the spatial distribution of the pore structure, the pore structure is arranged on the whole blade surface; 3) selecting pore structure parameters: the porosity is 0.5% -2%, the diameter of each pore is 0.1-2 mm, the distance between every two adjacent pores is 0.1-2 mm, and the depth of each pore is 0.1-2 mm; 4) the two-step method weaves the preform and forms a pore structure. Through reasonable in design's pore structure, realize that the transition in advance of low pressure turbine boundary layer is twisted, reach the effect that promotes the engine performance.
Description
Technical Field
The invention relates to the field of low-pressure turbines, in particular to a low-pressure turbine boundary layer forced transition method based on a macro pore structure.
Background
The aircraft engine is an important component of an aircraft, is known as the heart of the aircraft, and the performance of the aircraft engine directly influences and even determines the overall performance of the aircraft. The low-pressure turbine is one of the core components of an aircraft engine, and is generally used for driving a fan and a booster stage, and the overall performance of the engine is directly influenced by the aerodynamic efficiency. Due to the relative rotation among the blade rows, the flow of the blade surface in the low-pressure turbine is in a very complex environment, and has the unsteady effect of the flow and the disturbance of upstream wake, incoming flow turbulence and the like. In practical application, the engine size of some aircrafts is small, and the air is sparse during high-altitude flight, so that the flowing Reynolds number is extremely low, the flow on the surface of the blade is in a laminar flow state, and separation is easy to occur under a strong adverse pressure gradient to generate large aerodynamic loss, so that the working efficiency of the engine is reduced rapidly, and therefore, the improvement of the flow state on the surface of the low-pressure turbine blade is very important for improving the performance of the engine and further reducing the size of the engine.
Research shows that the key for determining the quality of the flow condition is whether the blade boundary layer is separated (aerodynamic loss caused by boundary layer separation is an important reason for reducing the efficiency of a low-pressure turbine and even an engine), so how to promote the advanced transition of the boundary layer flow and make the blade flow change from laminar flow to turbulent flow under the conditions of low Reynolds number and strong adverse pressure gradient has important significance in enhancing the separation resistance. For low reynolds number vane flow, Hourmouziadis is the first researcher to describe the development of the boundary layer of the vane in detail, and finds that under a large adverse pressure gradient, the boundary layer will be separated, which is embodied as that the flow forms a closed separation bubble or an open separation zone, and aerodynamic loss caused by flow separation is an important factor for the efficiency loss of the low-pressure turbine. To reduce aerodynamic losses, the open separation region or closed separation bubbles must be controlled, and this important finding points to improve turbine efficiency, such as by creating an unstable flow environment to control blade boundary layer separation and separation bubble size by triggering a transition in advance.
With the increase of thrust-weight ratio of aero-engines, the requirements for high-temperature resistant materials and cooling designs of turbine blades are increasingly strict, and the traditional high-temperature alloy materials are gradually replaced by composite materials with high temperature resistance and good mechanical properties. At present, aiming at manufacturing low-pressure turbine blades by composite materials, a related forced transition device design method is established by considering a transition mechanism under the condition of low Reynolds number, the method only considers the preparation of a composite material prefabricated body, and the reduction of hole-edge mechanical property caused by pores formed by the prefabricated body is a main problem existing in the design method, so that the problem of composite material failure is possibly caused, and the service life of an engine is shortened.
Disclosure of Invention
The invention aims to overcome the defects of a method for improving the flow state of the surface of a blade by using a low-pressure turbine blade in the prior art, provides a low-pressure turbine boundary layer forced transition method based on a macroscopic pore structure, realizes the advance transition of the low-pressure turbine boundary layer through designing a reasonable pore structure, and achieves the effect of improving the performance of an engine.
In order to achieve the purpose, the invention adopts the following technical scheme:
a low-pressure turbine boundary layer forced transition method based on a macro pore structure comprises the following steps:
1) selection of preform parameters
The weaving angle of the braided fabric preform is 25-45 degrees, the average diameter of the fiber is 9-15 mu m, the volume fraction of the fiber is 30-45%, the preform adopts an integral design, and the length of the blade body of the designed low-pressure turbine blade is increased by 0.3-0.6% relative to the blade body of the low-pressure turbine blade prepared from the high-temperature alloy.
2) Design of spatial distribution of pore structure
Because the low-pressure turbine blade is integrally woven by adopting a three-dimensional weaving method, the macro-pore structure is arranged on the whole blade surface.
3) Selection of pore structure parameters
The porosity is about 0.5% -2%, the diameter D of the unit macro-woven pores is 0.1-2 mm, the depth L of the unit macro-woven pores is 0.1-2 mm, the space S between adjacent unit macro-woven pores is 0.1-2 mm, and the values of the three are kept consistent. The parameters of the pore structure are based on the influence of the transverse elastic modulus and the transverse tensile strength of the composite material on the limiting conditions of the low-pressure turbine blade, such as thermal protection, structural strength, processing and manufacturing, and the like, and the proper porosity and pore size are selected by combining the forward transition effect.
4) Two-step method for knitting prefabricated body
Adopts a two-step weaving method in a three-dimensional weaving technology and combines circular weaving. Circular three-dimensional weaving means that the arrangement mode of weaving yarns on a machine chassis is circular, and a fabric with a circular cross section is woven. In the two-step weaving process, the yarn carriers are distributed in rows and columns on the weaving machine base plate, the preform is formed above, and one movement cycle is divided into two steps. The method comprises two yarn systems, one being a beam yarn and the other being a weaving yarn. In the first step of movement, the knitting yarns bind the axial yarns arranged along the axial direction together under the carrying action of the yarn carrier, and the knitting yarns move along the appointed direction, and the moving directions of the adjacent yarns are opposite; in the second step of movement, the knitting yarns move in a direction perpendicular to the direction indicated in the first step and the direction of movement of the adjacent yarns is opposite thereto. The two motion steps are a cycle, with the repeatedly woven yarns interwoven to form a low pressure turbine blade fabric.
5) Formation of pore structure
During the knitting process, the yarn arrangement is arranged according to the section shape of the knitting component, the axial yarn does not move, the fixed yarn is basically in a straight line in the structure along the forming direction (axial direction) of the knitting fabric and is distributed according to the section shape of the knitting fabric, the knitting yarn moves among the fixed yarn in a certain pattern, the fixed yarn is tightly tied by the tension of the knitting yarn so as to stabilize the section shape of the three-dimensional knitting fabric, the yarn is mutually interwoven and crossed, and macro knitting pores distributed in a staggered mode are gradually formed, and finally a non-layered space whole is formed.
Compared with the prior art, the technical scheme of the invention has the following beneficial effects:
the invention has simple structure and low application cost, and compared with other design methods, the invention can obviously reduce the aerodynamic loss on the low-pressure turbine blade, reduce the weight of the engine and improve the efficiency of the engine. Meanwhile, under the condition of low Reynolds number flow, the method can well trigger transition of the boundary layer of the blade surface in advance to convert the transition into a turbulent flow state, thereby improving the flow state of the blade surface and reducing the aerodynamic loss.
Because the low-pressure turbine blade is made of the three-dimensional woven composite material with the macroscopic pore structure, under the condition of low Reynolds number blade flow, the boundary layer of the low-pressure turbine is induced to transition before separation, and the fluid after transition has strong momentum, so that the separation resistance of the fluid is enhanced, the flow loss is reduced, and the efficiency of the engine is further improved. Compared with the traditional composite material structure, the three-dimensional woven composite material manufactured by adopting the three-dimensional weaving technology completely overcomes the defect of layering of the traditional composite material, and has the advantages of non-layering structure, strong structural designability, high specific strength, high specific modulus, high impact damage tolerance, good fatigue resistance, insensitivity to open pores and the like.
Drawings
Fig. 1 is a schematic view of a low-pressure turbine structure.
FIG. 2 is a schematic view of the distribution of macro-weave porosity on the surface of a low pressure turbine blade.
Figure 3 is a two-dimensional schematic of the macro-weave voids in the composite.
Figure 4 is a three-dimensional schematic representation of the macro-weave voids in a composite material.
Figure 5 is a schematic view of the cell macro-weave apertures.
FIG. 6 is a graph of the peak average turbulence energy within the boundary layer at a unit pore structure as a function of pore size.
FIG. 7 is a plot of the transverse modulus of elasticity of the composite as a function of porosity.
FIG. 8 is a plot of composite cross-directional tensile strength as a function of porosity.
Reference numerals: 1 denotes a low-pressure turbine disk; 2 denotes low pressure turbine blades; 3 denotes macro-weave apertures; 4 represents a axial yarn; 5 represents a knitting yarn; d represents the diameter of the unit macro-weave pores; s represents the spacing between adjacent unit macro-weave apertures; l represents the depth of the cell macro-weave voids.
Detailed Description
In order to make the technical problems, technical solutions and advantageous effects of the present invention clearer and clearer, the present invention is further described in detail below with reference to the accompanying drawings and embodiments.
Referring to fig. 1 to 8, the method for transition of the boundary layer of the low-pressure turbine based on the macro pore structure includes the steps of:
1) selection of preform parameters
The braid angle of the braided fabric preform is 25-45 degrees, the average diameter of the fibers is 9-15 mu m, the volume fraction of the fibers is 30% -45%, the preform is designed in an integral mode, the braided fabric preform has the advantages of being easy to seal and assemble, the limitation that a cooling system is needed when a high-temperature alloy material is adopted in the prior art is eliminated, and the thermal expansion coefficient matching can be considered for carrying out corresponding size adjustment. Comprehensively considered, the length of the blade body of the low-pressure turbine blade 2 is increased by 0.3-0.6 percent compared with the blade body of the low-pressure turbine blade prepared from the high-temperature alloy.
2) Design of spatial distribution of pore structure
Since the low-pressure turbine blade 2 is integrally woven by a three-dimensional weaving method for a composite low-pressure turbine blade, the macro-weave apertures 3 are arranged throughout the surface of the low-pressure turbine blade 2 as shown in fig. 2.
3) Selection of pore structure parameters
The porosity is about 0.5% -2%, the diameter D of the unit macro-woven pores is 0.1-2 mm, the depth L of the unit macro-woven pores is 0.1-2 mm, the space S between adjacent unit macro-woven pores is 0.1-2 mm, and the values of the three are kept consistent. The peak value of the average turbulence energy in the boundary layer at the cell pore structure is shown in fig. 6 along with the change of the pore size (the increase of the turbulence energy brings about greater pulsation, promotes the development instability of the boundary layer, and triggers transition in advance), the change of the transverse elastic modulus of the composite material along with the porosity is shown in fig. 7 (the transverse elastic modulus is reduced by about 1.35% for every 1% increase of the porosity), and the change of the transverse tensile strength of the composite material along with the porosity is shown in fig. 8 (the transverse tensile strength is reduced by about 3% for every 1% increase of the porosity).
4) Two-step method for knitting prefabricated body
The method adopts a three-dimensional weaving process, namely a two-step three-dimensional weaving process, and comprises two yarn systems, wherein one yarn system is a fixed axial yarn 4, and the other yarn system is a weaving yarn 5, and the axial line is tightened. The arrangement mode of the knitting yarns is circular by combining circular three-dimensional knitting, the yarn carriers are distributed on a base plate of the knitting machine in a row and column mode, the prefabricated member is formed above, and one movement cycle is divided into two steps. In the first step of movement, the knitting yarns bind the axial yarns arranged along the axial direction together under the carrying action of the yarn carrier, and the knitting yarns move along the appointed direction, and the moving directions of the adjacent yarns are opposite; in the second step of movement, the knitting yarns move in a direction perpendicular to the direction indicated in the first step and the direction of movement of the adjacent yarns is opposite thereto. This completes one cycle of the knitting motion and then the cycle repeats these two steps.
5) Formation of pore structure
The yarns continuously repeat the two movement steps of the two-step method, and the axial yarns are basically formed into a straight line in the structure along the forming direction (axial direction) of the three-dimensional braided fabric and are distributed according to the cross section shape of the main braided fabric; the knitting yarn moves among the axial yarns in a certain pattern, and the axial yarns are tightened by the tension of the knitting yarn, so that the cross section shape of the three-dimensional knitting is stabilized. Together with the corresponding clinching operation and fabric output motion, the yarns are more tightly interwoven together to form a final structure with macro-weave apertures in a staggered distribution as shown in figures 3-5.
Fig. 1 to 5 show details of the low-pressure turbine blade made of the SiC ceramic matrix composite based on the macro-pore structure design and the pores thereof, according to the embodiment of the present invention, the maximum service temperature can reach 1700 ℃, and the requirement of the advanced aero-engine on the working temperature can be satisfied. According to calculation, under the working conditions that the room temperature is 20 ℃ and the rotating speed is 12000rpm, the maximum stress value of the SiC ceramic matrix composite low-pressure turbine blade designed on the basis of the macro-pore structure along the transverse direction of the weaving yarns is 70 MPa. Comprehensively considering, the porosity of the designed composite material is 0.7%, the transverse tensile strength is 90MPa and is higher than the maximum tensile stress of 70MPa, the ratio of the two is 77.8%, and the strength requirement is met; the transverse elastic modulus is 97.5MPa, and the radial displacement value of the low-pressure turbine blade 2 and the low-pressure turbine disc 1 under the transverse elastic modulus is 2.44 multiplied by 10-5m is lower than the low-pressure vortex of the high-temperature alloy under the same size3.89X 10 of wheel parts-5m, meets the requirements of deformation and strength, and can not be in contact with the casing to generate abrasion. Under the condition that the mechanical property and the thermal fatigue property of the composite material meet the working requirement of the low-pressure turbine blade, the diameter of the macro-woven pores of the design unit is 2mm, the depth of the macro-woven pores of the unit is 2mm, and the distance between the macro-woven pores of adjacent units is 2mm, so that the transition effect is maximized.
Claims (8)
1. A low-pressure turbine boundary layer forced transition method based on a macro pore structure is characterized by comprising the following steps:
1) selecting parameters of the preform: the prefabricated body adopts an integral design, and the blade body length of the low-pressure turbine blade is increased by 0.3-0.6 percent relative to the blade body of the low-pressure turbine blade prepared from the high-temperature alloy;
2) design of spatial distribution of pore structure: the pore structure is arranged on the whole blade surface;
3) selecting pore structure parameters: the porosity is 0.5% -2%, and the pore diameter is 0.1-2 mm;
4) the two-step method weaves the preform and forms a pore structure.
2. The low-pressure turbine boundary layer forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: in the step 1), the knitting angle of the knitted fabric preform is 25-45 degrees.
3. The low-pressure turbine boundary layer forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: in the step 1), the average fiber diameter of the braided fabric preform is 9-15 μm, and the fiber volume fraction is 30% -45%.
4. The low-pressure turbine boundary layer forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: in the step 3), the distance between adjacent pores is 0.1-2 mm, and the depth of the pores is 0.1-2 mm.
5. The low-pressure turbine boundary layer forced transition method based on the macro-pore structure as claimed in claim 4, wherein: the values of the space between the adjacent pores, the depth of the pores and the diameter of the pores are consistent.
6. The low-pressure turbine boundary layer forced transition method based on the macro-pore structure as claimed in claim 1, characterized in that: and 4) adopting a two-step weaving method in a three-dimensional weaving technology and combining circular weaving.
7. The low-pressure turbine boundary layer forced transition method based on the macro-pore structure as claimed in claim 6, wherein: in step 4), in the two-step weaving process, the yarn carriers are distributed on a base plate of a weaving machine in a row and column mode, and the prefabricated member is formed above, so that one motion cycle is divided into two steps: in the first step of movement, under the carrying action of a yarn carrier, the knitting yarns bind the axial yarns which are arranged along the axial direction together, the knitting yarns move along the appointed direction, and the moving directions of the adjacent yarns are opposite; in the second step of movement, the knitting yarns move in a direction perpendicular to the direction indicated in the first step and the direction of movement of the adjacent yarns is opposite to the direction of movement; the two motion steps are a cycle, with the repeatedly woven yarns interwoven to form a low pressure turbine blade fabric.
8. The low-pressure turbine boundary layer forced transition method based on the macro-pore structure as claimed in claim 6, wherein: in the knitting process of the step 4), the yarn arrangement is arranged according to the section shape of the knitting component, the axial yarns do not move, the axial yarns are in a straight line in the structure along the forming direction of the knitting fabric and are distributed according to the section shape of the knitting fabric, the knitting yarns move among the axial yarns in a certain pattern, the axial yarns are tightly tied by the tension of the knitting yarns to stabilize the section shape of the three-dimensional knitting fabric, the yarns are mutually interwoven and crossed together, macro knitting pores distributed in a staggered mode are gradually formed, and finally a non-layered space whole is formed.
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Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030085324A1 (en) * | 1999-11-24 | 2003-05-08 | Lorenzo Battisti | Boundary layer control of aerodynamic airfoils |
| EP2065563A2 (en) * | 2007-11-29 | 2009-06-03 | United Technologies Corporation | Gas turbine engine systems involving mechanically alterable vane throat areas |
| CN106189631A (en) * | 2016-07-11 | 2016-12-07 | 复旦大学 | A kind of aircraft wing based on micro nano-coatings turns twists related method thereof |
| CN110481761A (en) * | 2019-08-20 | 2019-11-22 | 空气动力学国家重点实验室 | It is a kind of to utilize surface aperture/slot flow transition passive control device |
| CN112149236A (en) * | 2020-10-12 | 2020-12-29 | 南京航空航天大学 | Thermal analysis method of ceramic matrix composite turbine blade considering micro-woven structure and fiber bundle direction change |
-
2021
- 2021-08-26 CN CN202110986987.9A patent/CN113513370B/en active Active
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20030085324A1 (en) * | 1999-11-24 | 2003-05-08 | Lorenzo Battisti | Boundary layer control of aerodynamic airfoils |
| EP2065563A2 (en) * | 2007-11-29 | 2009-06-03 | United Technologies Corporation | Gas turbine engine systems involving mechanically alterable vane throat areas |
| CN106189631A (en) * | 2016-07-11 | 2016-12-07 | 复旦大学 | A kind of aircraft wing based on micro nano-coatings turns twists related method thereof |
| CN110481761A (en) * | 2019-08-20 | 2019-11-22 | 空气动力学国家重点实验室 | It is a kind of to utilize surface aperture/slot flow transition passive control device |
| CN112149236A (en) * | 2020-10-12 | 2020-12-29 | 南京航空航天大学 | Thermal analysis method of ceramic matrix composite turbine blade considering micro-woven structure and fiber bundle direction change |
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