A turbine guide vane anti-fouling structure and a turbine guide vane having the same

Abstract

The application provides a turbine guide vane anti-adhesion structure and a turbine guide vane with the same. The anti-adhesion structure comprises a corrugated structure covering at least a leading edge of the turbine guide vane, and a cold air guide pipe arranged in an inner cavity of the turbine guide vane. The corrugated structure is composed of a plurality of wave crests and wave troughs, and an impingement film hole is arranged between the wave crest and the wave trough. The impingement film hole is used for forming a film and impingement cooling on the outer wall surface of the corrugated structure. The cold air guide pipe is provided with an impingement hole, which is aligned with the wave crest area of the corrugated structure and used for impingement cooling of the corrugated structure. The application can reduce the influence of adhesion on the blade cooling structure, avoid blade ablation caused by film hole blockage, and prolong the service life of the blade.

Description

Technical Field

[0001] This application belongs to the field of aero-engine blade design technology, and specifically relates to a turbine guide blade anti-adhesion structure and a turbine guide blade having the same. Background Technology

[0002] Currently, the guide vanes of aero-engines and gas turbines feature a flat, smooth aerodynamic shape. The leading edge of the blades is designed with film cooling holes, and the internal structure employs an impact cooling system. When impurities and particles in the combustion gas enter the guide vane, they melt and adhere to the blade surface under high temperatures. This blocks the film cooling holes, disrupts the outflow of cool gas, and ultimately leads to overheating and ablation of the blade.

[0003] Existing turbine guide vanes employ a straight, smooth aerodynamic shape. The leading edge region of the blade surface is nearly perpendicular to the direction of the incoming gas flow. Aero engines often operate in atmospheric environments with high dust and particulate matter content. Impurities formed from the combustion of these substances easily adhere to and deposit on the leading edge and blade nose region, causing blockage of the film cooling pores and blade sintering, ultimately leading to blade failure. This reduces blade overhaul life and increases operating costs. Summary of the Invention

[0004] The purpose of this application is to provide a turbine guide vane anti-adhesion structure and a turbine guide vane having the same, in order to solve or mitigate at least one of the problems in the prior art.

[0005] The technical solution of this application is: a turbine guide vane anti-adhesion structure, comprising:

[0006] At least the corrugated structure covering the leading edge of the turbine guide vanes; and

[0007] Cooling gas duct installed inside the turbine guide vane;

[0008] The corrugated structure consists of several peaks and troughs, with impact air film holes provided between the peaks and troughs. These impact air film holes are used to form an air film and provide impact cooling on the outer wall of the corrugated structure. The cooling air duct is provided with impact holes, which are aligned with the peak areas of the corrugated structure for impact cooling of the corrugated structure.

[0009] In a preferred embodiment of this application, the corrugated structure covers the leading edge of the turbine guide vane and the front part of the vane basin.

[0010] In a preferred embodiment of this application, the direction of the corrugated structure is consistent with the direction of gas flow.

[0011] In a preferred embodiment of this application, the maximum undulation angle θ of the corrugated structure is ≤20°.

[0012] In a preferred embodiment of this application, the wave crest and the half-valleys on both sides of the wave crest constitute a corrugated unit, and the number of corrugated units in the turbine guide vane is no more than 6.

[0013] In a preferred embodiment of this application, the impact film hole faces the sidewall between adjacent wave crests and troughs, and the impact hole is perpendicular to the wall surface of the cold air duct.

[0014] In addition, this application also provides a turbine guide vane, the turbine guide vane including the turbine guide vane anti-adhesion structure as described in any of the above.

[0015] This application utilizes a corrugated structure, a wave crest without film cooling holes, and impact holes in the cooling ducts for impact cooling of the outer wall surface. This reduces the impact of deposits on the blade cooling structure, avoids blade ablation caused by film cooling hole blockage, and extends blade life. It is suitable for working environments with high atmospheric dust content. Attached Figure Description

[0016] To more clearly illustrate the technical solutions provided in this application, the accompanying drawings will be briefly described below. Obviously, the drawings described below are merely some embodiments of this application.

[0017] Figure 1 This is a schematic diagram of the cold airflow path for turbine guide vanes in existing technology.

[0018] Figure 2 This is a schematic diagram of the internal flow path of the turbine guide vane in this application.

[0019] Figure 3 This is a perspective view of the turbine guide vane of this application.

[0020] Figure 4 This is a schematic diagram of the anti-adhesion structure of this application.

[0021] Figure 5 This is a schematic diagram of the impact film covering the air film and the impact cooling area of ​​the present application.

[0022] Figure label:

[0023] 20-Turbine guide vane

[0024] 21-Corrugated Structure

[0025] 211-Impact film pore

[0026] 212-Corrugated Unit

[0027] 22-Air conditioning duct

[0028] 221-Impact Hole Detailed Implementation

[0029] To make the objectives, technical solutions, and advantages of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings.

[0030] To mitigate the deposition of deposits on the leading edge of turbine guide vanes and reduce the blockage of the leading edge film air holes by deposits, this application proposes an anti-deposit structure for turbine guide vanes. This structure can achieve impact cooling of the outer wall of the blade, reduce the temperature of the leading edge region of the blade, extend the service life of the blade, and at the same time prevent deposit deposition.

[0031] like Figures 2 to 5 As shown, the anti-adhesion structure for turbine guide vanes provided in this application includes: a corrugated structure 21 covering at least the leading edge of the blade and a cooling air duct 22 disposed inside the cavity of the turbine guide vane 20. The corrugated structure 21 is composed of a number of crests and troughs, and an impact film hole 211 is provided between the crests and troughs. The impact film hole 211 faces the sidewall between adjacent crests and troughs. An impact hole 221 is arranged on the cooling air duct 22, which is aligned with the crest area of ​​the corrugated structure and is perpendicular to the wall of the cooling air duct 22.

[0032] In a preferred embodiment of this application, the corrugated structure 21 covers the leading edge and the front region of the turbine guide vane, which reduces the angle between the incoming gas flow Q1 and the blade wall, thereby reducing the normal impulse of impurity particles in the gas flow on the blade surface and helping to alleviate the adhesion and deposition on the blade surface.

[0033] Furthermore, the corrugated structure 21 is aligned with the gas flow direction, with a maximum undulation angle θ ≤ 20°, thereby reducing the adverse effects of this structure on turbine performance and cooling.

[0034] Combination Figure 4 As shown, the crest and the half-valleys on both sides constitute the corrugated unit 212, and the number of corrugated units 212 in a single turbine guide vane is no more than 6.

[0035] Combination Figure 4 and Figure 5 As shown, after the cold air Q2 enters the cold air duct 22 and flows out, it flows out from the impact hole 221. The cold air Q2 impacts the inner wall surface of the cooling blade crest, which enhances the cooling of the crest area. Then, the cold air flows along the wall surface between the crest and the trough and flows out from the impact air film hole 221. The cold air forms an air film covering the outer wall surface S1 between the impact air film hole 221 and the trough of the corrugated unit, and forms impact cooling on the outer wall surface S2 between the trough and the impact air film hole of the adjacent corrugated unit.

[0036] In the overall deposition of deposits on turbine guide vanes, the deposition is most severe in the peak area of ​​the blade. However, since this application does not provide air film pores in this area, the deposition of deposits will not damage the cooling structure. At the trough, the air film coverage and the impact cooling effect are superimposed, which helps to reduce the temperature of the outer wall surface.

[0037] For the anti-adhesion structure of this application, assuming that the gas particles collide head-on with the blade wall, the particle mass is m, and the velocity is v, then the normal impulse I of the particle acting on the blade wall is... 90 =mv, corresponding to kinetic energy Ek 90 =m·v 2 / 2; Assuming the gas flow direction is the same, and particles of the same size and velocity act on a corrugated surface with θ = 20°, then the normal impulse I of the particles acting on the blade wall is... 20 =mv·cos20°, corresponding to kinetic energy Ek 20 =m(v·cos20°)2 / 2=m·v 2 Compared to a head-on collision, the energy is reduced by 10%.

[0038] In addition, this application also provides a turbine guide vane having the above-mentioned anti-adhesion structure.

[0039] This application utilizes a corrugated structure, a wave crest without film cooling holes, and impact holes in the cooling ducts for impact cooling of the outer wall surface. This reduces the impact of deposits on the blade cooling structure, avoids blade ablation caused by film cooling hole blockage, and extends blade life. It is suitable for working environments with high atmospheric dust content.

[0040] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. A turbine guide vane anti-adhesion structure, characterized in that, include: The corrugated structure at least covers the leading edge of the turbine guide vane; and Cooling gas duct installed inside the turbine guide vane; The corrugated structure consists of several peaks and troughs, with impact air film holes provided between the peaks and troughs. These impact air film holes are used to form an air film and provide impact cooling on the outer wall of the corrugated structure. The cooling air duct is provided with impact holes, which are aligned with the peak areas of the corrugated structure for impact cooling of the corrugated structure.

2. The turbine guide vane anti-adhesion structure as described in claim 1, characterized in that, The corrugated structure covers the leading edge of the turbine guide vane and the front part of the vane basin.

3. The turbine guide vane anti-adhesion structure as described in claim 1, characterized in that, The direction of the corrugated structure is consistent with the direction of gas flow.

4. The turbine guide vane anti-adhesion structure as described in claim 3, characterized in that, The maximum undulation angle θ of the corrugated structure is ≤20°.

5. The turbine guide vane anti-adhesion structure as described in claim 1, characterized in that, The wave crest and the half-valleys on both sides of the wave crest constitute a corrugated unit, and the number of corrugated units in the turbine guide vane is no more than 6.

6. The turbine guide vane anti-adhesion structure as described in claim 1, characterized in that, The impact film hole faces the sidewall between adjacent wave crests and troughs, and the impact hole is perpendicular to the wall of the cold air duct.

7. A turbine guide vane, characterized in that, The turbine guide vane includes the turbine guide vane anti-adhesion structure as described in any one of claims 1 to 6.

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