WO2020220498A1 - Low-pressure turbine blade having wavy suction surface - Google Patents
Low-pressure turbine blade having wavy suction surface Download PDFInfo
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- WO2020220498A1 WO2020220498A1 PCT/CN2019/099411 CN2019099411W WO2020220498A1 WO 2020220498 A1 WO2020220498 A1 WO 2020220498A1 CN 2019099411 W CN2019099411 W CN 2019099411W WO 2020220498 A1 WO2020220498 A1 WO 2020220498A1
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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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- the invention relates to the technical field of civil aviation, in particular to a low-pressure turbine blade with a wavy suction surface, which is suitable for high-load and ultra-high-load low-pressure turbine blades of aero engines.
- the aero engine is known as the "Flower of Industry” and is the embodiment of a country's comprehensive national strength.
- Low-pressure turbine is one of the important parts of aero engine, its weight is about 25% of the weight of the whole machine, and the cost is about 15% of the cost of the whole machine. If the efficiency of the low-pressure turbine is increased by 1%, the oil consumption of the whole machine will be reduced by 0.5%-1.0%.
- the main way to improve the performance of the low-pressure turbine has shifted from the aerodynamic performance of a single blade to improving the overall performance of the low-pressure turbine. It mainly includes: increasing the load of a single blade, reducing the number of blades, reducing the weight of the low-pressure turbine, and then reducing the overall cost (manufacturing cost and Flight cost). However, increasing the load of low-pressure turbine blades will increase the risk of boundary layer separation, and even open separation. If the design is slightly deviated, the ultra-high-load low-pressure turbine will greatly increase the fuel consumption rate and overall cost. Due to conservative design and to avoid boundary layer separation, traditional low-pressure turbine design loads are relatively low. However, in recent years, companies such as Rolls-Royce/GE have tried to adopt the design concept of ultra-high-load low-pressure turbines. The design of ultra-high-load low-pressure turbines will greatly reduce the number of blades and the weight of the turbine.
- ultra-high-load low-pressure turbines can greatly reduce the number of blades and the weight of low-pressure turbines
- studies have found that compared with traditional blades, ultra-high-load blades are more difficult to maintain high efficiency operation under all working conditions.
- researchers have begun to use flow control methods to suppress separation bubbles and secondary flow losses on the suction surface of low-pressure turbines.
- the existing flow control schemes are divided into two categories: active control and passive control.
- Active control methods include flow direction momentum injection, boundary layer suction, flow direction vortex generation and excitation instability.
- Passive control includes vortex generators, endwall fences, and thickening of the junction between the leading edge of the blade and the end wall.
- the invention belongs to a passive separation method, which utilizes a wave-shaped suction surface to generate a counter-turning vortex, enhances the momentum exchange between the main flow and the boundary layer, and finally suppresses the generation of separation bubbles on the suction surface of the ultra-high load low-pressure turbine, suppresses loss, and reduces the backward angle.
- the suction surface fluid is easy to separate and the loss is increased.
- the present invention provides a low-pressure turbine blade with a wave-shaped suction surface. The wave-shaped setting is added on the suction surface, which can reduce the loss caused by separation bubbles, thereby improving turbine efficiency.
- a low-pressure turbine blade with a wavy suction surface which is suitable for reducing the blade shape loss of aero-engine high-load and ultra-high-load low-pressure turbine blades.
- the low-pressure turbine blade includes the front of the blade.
- the shape of the suction side of the blade is a wave surface extending along the height of the blade. The wave surface starts at the leading edge of the blade and ends at the trailing edge of the blade.
- the wave surface consists of the peak and the trailing edge of the blade.
- the wave troughs are alternately connected.
- the distance between the wave crest and the trough along the cascade pitch direction changes linearly from 0 to 2A, and then linearly decreases from 2A to 0, where A is The maximum amplitude of the wave crest surface and the trough surface, and the maximum amplitude is the fluid separation position.
- the shape of an interface of the wave surface along the blade height direction is a sine wave.
- the surface wave shape of the low-pressure turbine blade provided by the present invention forms a counter-rotating vortex near the trailing edge, and the low-energy part is substituted into the main flow through the counter-rotating vortex, effectively strengthening the kinetic energy exchange between the main flow and the boundary layer , Increase the kinetic energy of the boundary layer, suppress the formation of separation bubbles, and transform the original separation loss into a lower loss of the counter-rotating vortex loss.
- the average airflow deviation angle and loss coefficient at the trailing edge are smaller than the original turbine blades. Realize the improvement of low pressure turbine performance.
- Figure 1 is a schematic diagram of the original blade shape, wave crest blade shape and wave trough blade shape of the low-pressure turbine blade provided by the present invention
- Figure 2 is a three-dimensional schematic diagram of a low-pressure turbine blade provided by the present invention.
- Figure 3 is a front view of the low-pressure turbine blade provided by the present invention.
- Figure 4 is a perspective view of a low-pressure turbine blade provided by the present invention.
- the invention provides a low-pressure turbine blade with a wavy suction surface, which is suitable for reducing the blade shape loss of aero-engine high-load and ultra-high-load low-pressure turbine blades.
- the low-pressure turbine blade includes a blade leading edge 1, a blade suction side 2, and a blade pressure Side 3 and the trailing edge 4 of the blade.
- the shape of the suction side 2 of the blade is a wavy surface extending along the height of the blade. The wavy surface starts from the leading edge 1 of the blade and ends at the trailing edge 4 of the blade.
- the wave crests and troughs of the wavy surface are connected alternately From the leading edge of the blade to the trailing edge of the blade, the distance between the crest and trough of the wave surface along the cascade pitch direction changes linearly from 0 to 2A, and then linearly decreases from 2A to 0, where A is the peak surface and The maximum amplitude of the trough surface, where the maximum amplitude is the fluid separation position.
- the above-mentioned wave crest profile 6 and trough profile 7 are alternately arranged along the blade height direction, and finally obtain a low-loss low-loss turbine blade with a wave-shaped suction surface, as shown in FIG. 4.
- the working principle of the blade structure for improving the performance of the low-pressure turbine provided by the present invention is described as follows: the low-pressure turbine blade that flows through this structure generates multiple sets of counter-turning vortices in the fluid through the wave protrusions, and increases the energy exchange between the main flow and the boundary layer. Achieve the effect of inhibiting separation bubbles.
- the loss changes from the original boundary separation loss to the vortex loss.
- the local position loss is greater than the original blade loss here, but the average loss decreases.
- the airflow deviation angle also increases locally, but the overall decrease phenomenon.
- the wavy blade does not reduce the secondary flow loss on the end wall, and only works in the two-dimensional flow region.
Abstract
A low-pressure turbine blade having a wavy suction surface, applicable to reducing profile loss of a high-load low-pressure turbine blade and an ultra-high-load low-pressure turbine blade on an aero engine. The low-pressure turbine blade comprises a blade leading edge (1), a blade suction side (2), a blade pressure side (3), and a blade trailing edge (4). The shape of the blade suction side (2) is a wavy surface extending in a height direction of the blade. The wavy surface starts at the blade leading edge (1), and ends at the blade trailing edge (4). The wavy surface is formed by alternately arranging crests and troughs. From the blade leading edge (1) to the blade trailing edge (4), the distance between the wavy crest and the wavy trough in a vane pitch direction increases linearly from 0 to 2A and decreases linearly from 2A to 0, where A is the greatest amplitude of the wavy surface. Fluid separates from the blade in the position corresponding to the greatest amplitude. The blade structure effectively reduces separation of the fluid from the blade, reduces loss, and improves the performance of a low-pressure turbine.
Description
本发明涉及民用航空技术领域，尤其涉及一种吸力面波浪形的低压涡轮叶片，适用于航空发动机高负荷及超高负荷低压涡轮叶片。The invention relates to the technical field of civil aviation, in particular to a low-pressure turbine blade with a wavy suction surface, which is suitable for high-load and ultra-high-load low-pressure turbine blades of aero engines.
航空发动机被誉为“工业之花”，是一个国家综合国力的体现。低压涡轮是航空发动机的重要部件之一，其重量约为整机重量的25％，成本约为整机成本的15％。如低压涡轮效率提高1％，整机油耗将降低0.5％-1.0％。The aero engine is known as the "Flower of Industry" and is the embodiment of a country's comprehensive national strength. Low-pressure turbine is one of the important parts of aero engine, its weight is about 25% of the weight of the whole machine, and the cost is about 15% of the cost of the whole machine. If the efficiency of the low-pressure turbine is increased by 1%, the oil consumption of the whole machine will be reduced by 0.5%-1.0%.
现今，低压涡轮效率已超过90％，对其进一步提高已十分困难。对低压涡轮性能提升的主要方式已从单个叶片的气动性能转移到提高低压涡轮的综合性能，其主要包括：提高单个叶片载荷，减少叶片数量，降低低压涡轮重量，进而降低综合成本(制造成本和飞行成本)。然而，提高低压涡轮叶片载荷将增大边界层分离风险，甚至出现开式分离。如设计稍有偏差，超高载荷低压涡轮会大幅增加耗油率和综合成本。出于保守设计，为避免边界层发生分离，传统低压涡轮设计负荷相对较低。但近年来，罗罗/GE等公司尝试采用超高负荷低压涡轮设计理念，超高负荷低压涡轮的设计将大幅降低叶片数量和涡轮重量。Today, the efficiency of the low-pressure turbine has exceeded 90%, and it is very difficult to further improve it. The main way to improve the performance of the low-pressure turbine has shifted from the aerodynamic performance of a single blade to improving the overall performance of the low-pressure turbine. It mainly includes: increasing the load of a single blade, reducing the number of blades, reducing the weight of the low-pressure turbine, and then reducing the overall cost (manufacturing cost and Flight cost). However, increasing the load of low-pressure turbine blades will increase the risk of boundary layer separation, and even open separation. If the design is slightly deviated, the ultra-high-load low-pressure turbine will greatly increase the fuel consumption rate and overall cost. Due to conservative design and to avoid boundary layer separation, traditional low-pressure turbine design loads are relatively low. However, in recent years, companies such as Rolls-Royce/GE have tried to adopt the design concept of ultra-high-load low-pressure turbines. The design of ultra-high-load low-pressure turbines will greatly reduce the number of blades and the weight of the turbine.
超高载荷低压涡轮虽能大幅降低叶片数量及低压涡轮重量，但研究发现相对传统叶片，超高载荷叶片较难在所有工况下保持高效率运行。已有研究人员开始利用流动控制方法，抑制低压涡轮吸力面分离泡及二次流损失。现有的流动控制方案分为主动控制和被动控制两大类。主动控制有流向动量注入，边界层抽吸，流向涡生成和激发不稳定性等方法。被动控制有涡生成器，端壁拦截(endwall fence)，叶片前缘与端壁面交接处增厚等。本发明属于被动分离方法，利用波浪型吸力面，产生对转涡，增强主流与边界层的动量交换，最终抑制超高载荷低压涡轮吸力面上分离泡的生成，抑制损失，降低落后角。Although ultra-high-load low-pressure turbines can greatly reduce the number of blades and the weight of low-pressure turbines, studies have found that compared with traditional blades, ultra-high-load blades are more difficult to maintain high efficiency operation under all working conditions. Researchers have begun to use flow control methods to suppress separation bubbles and secondary flow losses on the suction surface of low-pressure turbines. The existing flow control schemes are divided into two categories: active control and passive control. Active control methods include flow direction momentum injection, boundary layer suction, flow direction vortex generation and excitation instability. Passive control includes vortex generators, endwall fences, and thickening of the junction between the leading edge of the blade and the end wall. The invention belongs to a passive separation method, which utilizes a wave-shaped suction surface to generate a counter-turning vortex, enhances the momentum exchange between the main flow and the boundary layer, and finally suppresses the generation of separation bubbles on the suction surface of the ultra-high load low-pressure turbine, suppresses loss, and reduces the backward angle.
发明内容Summary of the invention
为了克服航空发动机高负荷及超高负荷低压涡轮在低雷诺数工况下运行吸力面流体易于分离，损失加剧的问题。本发明提供一种吸力面波浪形的低压涡轮叶片，在吸力面增加波浪形设置，可以降低分离泡带来的损失，从而提高涡轮效率。In order to overcome the problem of aero-engine high-load and ultra-high-load low-pressure turbine operating under low Reynolds number conditions, the suction surface fluid is easy to separate and the loss is increased. The present invention provides a low-pressure turbine blade with a wave-shaped suction surface. The wave-shaped setting is added on the suction surface, which can reduce the loss caused by separation bubbles, thereby improving turbine efficiency.
为了达到上述目的，通过以下技术方案来实现的：一种吸力面波浪形的低压涡轮叶片，适用于降低航空发动机高负荷及超高负荷低压涡轮叶片叶型损失，所述低压涡轮叶片包括叶片前缘、叶片吸力侧、叶片压力侧和叶片尾缘，所述的叶片吸力侧的形状为沿叶高方向延伸的波浪面，波浪面始于叶片前缘，终于叶片尾缘，波浪面由波峰和波谷交替衔接而成，从叶 片前缘到叶片尾缘，波浪面的波峰和波谷之间沿叶栅距方向的距离变化为从0到2A线性增加，再从2A到0线性减少，其中A为波峰面和波谷面的最大振幅，最大振幅处为流体分离位置。In order to achieve the above purpose, the following technical solutions are implemented: a low-pressure turbine blade with a wavy suction surface, which is suitable for reducing the blade shape loss of aero-engine high-load and ultra-high-load low-pressure turbine blades. The low-pressure turbine blade includes the front of the blade. The shape of the suction side of the blade is a wave surface extending along the height of the blade. The wave surface starts at the leading edge of the blade and ends at the trailing edge of the blade. The wave surface consists of the peak and the trailing edge of the blade. The wave troughs are alternately connected. From the leading edge of the blade to the trailing edge of the blade, the distance between the wave crest and the trough along the cascade pitch direction changes linearly from 0 to 2A, and then linearly decreases from 2A to 0, where A is The maximum amplitude of the wave crest surface and the trough surface, and the maximum amplitude is the fluid separation position.
优选的，所述波浪面沿叶高方向的一个界面的形状为正弦波。Preferably, the shape of an interface of the wave surface along the blade height direction is a sine wave.
本发明的有益效果是：本发明提供的低压涡轮叶片表面波浪形状在尾缘附近形成对转涡，将能量低的部分通过对转涡代入主流中，有效强化主流与边界层之间的动能交换，增加边界层动能，抑制分离泡生成，将原来分离损失转变成损失更低的对转涡损失，同时由于对转涡的存在，尾缘处平均气流偏离角和损失系数比原来涡轮叶片小，实现低压涡轮性能的提升。The beneficial effects of the present invention are: the surface wave shape of the low-pressure turbine blade provided by the present invention forms a counter-rotating vortex near the trailing edge, and the low-energy part is substituted into the main flow through the counter-rotating vortex, effectively strengthening the kinetic energy exchange between the main flow and the boundary layer , Increase the kinetic energy of the boundary layer, suppress the formation of separation bubbles, and transform the original separation loss into a lower loss of the counter-rotating vortex loss. At the same time, due to the existence of the counter-rotating vortex, the average airflow deviation angle and loss coefficient at the trailing edge are smaller than the original turbine blades. Realize the improvement of low pressure turbine performance.
图1为本发明提供的低压涡轮叶片原有叶型、波峰叶型和波谷叶型示意图；Figure 1 is a schematic diagram of the original blade shape, wave crest blade shape and wave trough blade shape of the low-pressure turbine blade provided by the present invention;
图2为本发明提供的低压涡轮叶片三维示意图；Figure 2 is a three-dimensional schematic diagram of a low-pressure turbine blade provided by the present invention;
图3为本发明提供的低压涡轮叶片主视图；Figure 3 is a front view of the low-pressure turbine blade provided by the present invention;
图4为本发明提供的低压涡轮叶片立体图。Figure 4 is a perspective view of a low-pressure turbine blade provided by the present invention.
为使本发明的目的、技术方案及优点更加清楚明白，下面结合附图和具体实施例对本发明的低压涡轮叶片进行详细说明。In order to make the objectives, technical solutions, and advantages of the present invention clearer, the low-pressure turbine blade of the present invention will be described in detail below with reference to the drawings and specific embodiments.
本发明提供一种吸力面波浪形的低压涡轮叶片，适用于降低航空发动机高负荷及超高负荷低压涡轮叶片叶型损失，所述低压涡轮叶片包括叶片前缘1、叶片吸力侧2、叶片压力侧3和叶片尾缘4，所述的叶片吸力侧2的形状为沿叶高方向延伸的波浪面，波浪面始于叶片前缘1，终于叶片尾缘4，波浪面的波峰和波谷交替衔接而成，从叶片前缘到叶片尾缘，波浪面的波峰和波谷之间沿叶栅距方向的距离变化为从0到2A线性增加，再从2A到0线性减少，其中A为波峰面和波谷面的最大振幅，最大振幅处为流体分离位置。The invention provides a low-pressure turbine blade with a wavy suction surface, which is suitable for reducing the blade shape loss of aero-engine high-load and ultra-high-load low-pressure turbine blades. The low-pressure turbine blade includes a blade leading edge 1, a blade suction side 2, and a blade pressure Side 3 and the trailing edge 4 of the blade. The shape of the suction side 2 of the blade is a wavy surface extending along the height of the blade. The wavy surface starts from the leading edge 1 of the blade and ends at the trailing edge 4 of the blade. The wave crests and troughs of the wavy surface are connected alternately From the leading edge of the blade to the trailing edge of the blade, the distance between the crest and trough of the wave surface along the cascade pitch direction changes linearly from 0 to 2A, and then linearly decreases from 2A to 0, where A is the peak surface and The maximum amplitude of the trough surface, where the maximum amplitude is the fluid separation position.
下面本发明提供的一种吸力面波浪形的低压涡轮叶片的设计思路，当然不限于以下描述的；如图1-图3所示，本实施例中本发明提供的叶型通过原有叶片二维叶型5为参照，得到波峰叶型6和波谷叶型7。首先，确定流体分离位置(0.6C
x，C
x为轴向弦长)，该位置由原始叶型的叶栅实验或数值模拟确定，然后由该位置沿叶栅方向距离叶片外侧A得到点P(图1)，过该点做一条分别过前缘和尾缘的曲线，该曲线与原二维叶型5吸力侧之间的距离由前缘到分离位置线性增加，再由分离位置到尾缘线性减少，形成的曲线与压力侧曲线连成的封闭曲线称为波峰叶型6。在得到的波峰叶型6基础上，沿叶高方向距离半个波长(λ/2)位置，在该位置以原二维叶型5为基准，在分离位置沿叶栅方向距离叶片内侧长度为A得到点T(图1)，通过T点得到的叶型称为波谷叶型7。以上所述的波峰叶型6和波谷叶型7，沿叶高方向交替设置，最终得到吸 力面带有波浪型的降低损失低压涡轮叶片，如图4所示。
The design idea of a low-pressure turbine blade with a wavy suction surface provided by the present invention is of course not limited to the following description; as shown in Figures 1 to 3, the blade profile provided by the present invention in this embodiment passes through the two original blades. The dimensional leaf type 5 was used as a reference, and the peak leaf type 6 and the wave trough leaf type 7 were obtained. First, determine the fluid separation position (0.6C x , C x is the axial chord length), which is determined by the cascade experiment or numerical simulation of the original blade shape, and then the point P is obtained from the position along the cascade direction from the outer side A of the blade (Figure 1), make a curve passing through the leading edge and trailing edge respectively, the distance between this curve and the suction side of the original two-dimensional leaf profile 5 increases linearly from the leading edge to the separation position, and then from the separation position to the tail The edge decreases linearly, and the closed curve formed by connecting the curve and the pressure side curve is called the wave crest shape 6. On the basis of the obtained wave peak profile 6, the distance along the blade height direction by half a wavelength (λ/2) position, at this position based on the original two-dimensional profile 5, the distance from the inner side of the blade along the cascade direction at the separation position is A gets point T (Figure 1), and the leaf shape obtained from point T is called valley leaf shape 7. The above-mentioned wave crest profile 6 and trough profile 7 are alternately arranged along the blade height direction, and finally obtain a low-loss low-loss turbine blade with a wave-shaped suction surface, as shown in FIG. 4.
现将本发明提供的提高低压涡轮性能叶片结构的工作原理阐述如下：来流经过这种结构的低压涡轮叶片，通过波浪突起在流体中产生多组对转涡，增加主流与边界层能量交换，达到抑制分离泡的效果。在叶片尾缘位置，损失由原来的边界分离损失转变对转涡损失，局部位置损失大于原来叶片在此处的损失，但是平均损失下降，气流偏离角也存在局部变大，但整体减小的现象。波浪形叶片未减小端壁二次流损失，仅在二维流动区域起作用。The working principle of the blade structure for improving the performance of the low-pressure turbine provided by the present invention is described as follows: the low-pressure turbine blade that flows through this structure generates multiple sets of counter-turning vortices in the fluid through the wave protrusions, and increases the energy exchange between the main flow and the boundary layer. Achieve the effect of inhibiting separation bubbles. At the trailing edge of the blade, the loss changes from the original boundary separation loss to the vortex loss. The local position loss is greater than the original blade loss here, but the average loss decreases. The airflow deviation angle also increases locally, but the overall decrease phenomenon. The wavy blade does not reduce the secondary flow loss on the end wall, and only works in the two-dimensional flow region.
以上所述仅为本发明的优选实施例，并非因此限制本发明的专利范围，凡是利用本发明说明书及附图内容所作的等效结构或等效流程变换，或直接或间接运用在其他相关的技术领域，均同理包括在本发明的专利保护范围内。The above are only the preferred embodiments of the present invention, and do not limit the scope of the present invention. Any equivalent structure or equivalent process transformation made by using the content of the description and drawings of the present invention, or directly or indirectly applied to other related The technical field is also included in the scope of patent protection of the present invention.
Claims (2)
- 一种吸力面波浪形的低压涡轮叶片，适用于降低航空发动机高负荷及超高负荷低压涡轮叶片叶型损失，所述低压涡轮叶片包括叶片前缘、叶片吸力侧、叶片压力侧和叶片尾缘等，其特征是：所述的叶片吸力侧的形状为沿叶高方向延伸的波浪面，波浪面始于叶片前缘，终于叶片尾缘，波浪面的波峰和波谷交替衔接而成，从叶片前缘到叶片尾缘，波浪面的波峰和波谷之间沿叶栅距方向的距离变化为从0到2A线性增加，再从2A到0线性减少，其中A为波浪面的最大振幅，最大振幅处为流体分离位置。A low-pressure turbine blade with a wavy suction surface, which is suitable for reducing the blade shape loss of aero-engine high-load and ultra-high-load low-pressure turbine blades. The low-pressure turbine blade includes a blade leading edge, a blade suction side, a blade pressure side and a blade trailing edge The characteristic is that the shape of the suction side of the blade is a wavy surface extending along the height of the blade. The wavy surface starts at the leading edge of the blade and ends at the trailing edge of the blade. The wave crests and troughs of the wavy surface are alternately connected. From the leading edge to the trailing edge of the blade, the distance between the crest and trough of the wave surface along the cascade pitch direction changes linearly from 0 to 2A, and then linearly decreases from 2A to 0, where A is the maximum amplitude of the wave surface, the maximum amplitude The position is the fluid separation position.
- 根据权利要求1所述的一种吸力面波浪形的低压涡轮叶片，其特征在于，所述波浪面沿叶高方向的一个截面的形状为正弦形或余弦形。The low-pressure turbine blade with a wave-shaped suction surface according to claim 1, wherein the shape of a cross-section of the wave surface along the blade height direction is a sine shape or a cosine shape.
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| CN113847277B (en) * | 2021-10-17 | 2023-06-23 | 西北工业大学 | Supersonic porous adsorption type compressor blade with corrugated grooves on suction surface |
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