A cooling structure for a gas turbine stator vane of an aero turboshaft engine

Abstract

The utility model provides a kind of gas turbine stator guide vane cooling structure for aviation turboshaft engine, including stator guide vane;Further include: cooling sleeve, the inside of stator guide vane is provided with inner chamber;The cooling sleeve is arranged in inner chamber;Multiple cooling holes are opened in the leading edge end of the cooling sleeve, and cooling hole is close to the leading edge of stator guide vane;The upper end of the cooling sleeve is provided with inlet, and annular baffle shoulder is provided at inlet;Split joint is provided at the trailing edge of stator guide vane;Multiple spoiler columns are provided on the side of inner chamber close to the trailing edge of stator guide vane.It integrates impact cooling, convection cooling and split joint cooling, forms efficient phased cooling path, to make full use of the cooling potential of cooling airflow, significantly improves cooling efficiency, realizes the uniform, efficient cooling from leading edge to trailing edge, significantly improves the life of guide vane and the reliability of engine.

Description

Technical Field

[0001] This utility model relates to the field of aircraft turboshaft engines, and in particular to a cooling structure for the stator guide vanes of a gas turbine in an aircraft turboshaft engine. Background Technology

[0002] With the ever-increasing performance requirements of aero-engines, turbine inlet temperatures are rising continuously, posing a significant challenge to the cooling of turbine stator guide vanes. As a key component of gas turbines, stator guide vanes are directly exposed to high-temperature exhaust gases in an extremely harsh working environment, requiring efficient cooling technologies to ensure their service life and reliability.

[0003] Traditional turbine stator blade cooling technologies mainly employ three methods: convection cooling, impingement cooling, and film cooling. While these technologies are widely used, they still have significant limitations: convection cooling suffers from low efficiency; impingement cooling suffers from insufficient uniformity; and film cooling requires a large amount of cooling air drawn from the compressor, which significantly impacts overall engine performance. In existing technologies, stator blades are often designed with a simple hollow structure, resulting in limited contact area between the cooling airflow and the blade's inner wall, leading to low heat exchange efficiency.

[0004] Therefore, a cooling structure for the stator guide vanes of a gas turbine in an aero-turboshaft engine is provided to address the above-mentioned problems. Utility Model Content

[0005] This invention addresses the following technical problems: Existing stator guide vanes have low cooling efficiency; the limited contact area between the cooling airflow and the inner wall of traditional hollow blades results in insufficient heat exchange and poor cooling performance; uneven cooling airflow distribution, with multiple impact cooling streams interfering, intersecting, and colliding, leading to turbulent flow and kinetic energy loss, thus reducing cooling effectiveness; insufficient cooling in the trailing edge region, as the blade trailing edge structure is weak and difficult for cooling airflow to reach, easily generating localized high-temperature points, causing coating peeling, metal bulging, cracks, and even burn-through; and high cooling air consumption, with traditional film cooling technology requiring large amounts of air drawn from the compressor, affecting overall engine performance. Therefore, this invention provides a cooling structure for gas turbine stator guide vanes in aero-turboshaft engines.

[0006] This utility model solves the above-mentioned technical problems through the following technical solution:

[0007] This utility model provides a cooling structure for a gas turbine stator guide vane of an aero-turboshaft engine, including a stator guide vane; and further including: a cooling sleeve, wherein the stator guide vane has an inner cavity; the cooling sleeve is disposed in the inner cavity; the leading edge of the cooling sleeve has multiple cooling holes, and the cooling holes are close to the leading edge of the stator guide vane; the upper end of the cooling sleeve has an inlet, and the inlet has an annular shoulder; the trailing edge of the stator guide vane has a slit; and the inner cavity has multiple turbulence columns on the side near the trailing edge of the stator guide vane.

[0008] Preferably, the outer wall of the cooling sleeve and the inner cavity wall form an annular gap.

[0009] Preferably, the plurality of cooling holes are evenly divided into four rows, and the four rows of cooling holes are distributed at equal intervals to the front edge of the cooling sleeve.

[0010] Preferably, there are multiple slits, and each of the multiple slits is aligned with a multiple turbulence column.

[0011] Preferably, the inlet cross-section is larger than the total area of ​​the plurality of cooling holes.

[0012] Preferably, the wall thickness of the cooling sleeve is 0.5 mm.

[0013] Preferably, it further includes a positioning mechanism, which consists of four ribs disposed on the inner cavity sidewall.

[0014] Preferably, the four ribs are attached to the outer wall of the cooling sleeve.

[0015] Preferably, the shoulder covers and adheres to the upper end face of the inner cavity to seal the upper end of the inner cavity.

[0016] Preferably, the shoulder is welded to the upper end of the stator guide vane, and a sealing weld is formed at the position where the shoulder contacts the upper end of the stator guide vane.

[0017] Based on common knowledge in the field, the above-mentioned preferred conditions can be combined arbitrarily to obtain various preferred embodiments of this utility model.

[0018] The positive and progressive effects of this utility model are as follows:

[0019] The proposed cooling structure for the stator guide vanes of a gas turbine in an aero-turboshaft engine significantly improves cooling efficiency. It achieves comprehensive and efficient cooling through a combined cooling scheme of leading-edge impact cooling, internal convection cooling, and trailing-edge slit cooling. The cooling airflow first exits from the cooling holes on the cooling sleeve, providing concentrated impact cooling to the leading edge of the stator guide vane. Subsequently, the airflow flows towards the trailing edge along the annular gap between the inner wall of the cavity and the outer wall of the cooling sleeve, fully utilizing the heat exchange area. Finally, the airflow enhances heat transfer through the turbulence column region and exits from the trailing-edge slit, forming a complete and efficient cooling process.

[0020] The optimized cooling airflow distribution, with four rows of cooling holes at the leading edge of the cooling sleeve, ensures uniform impact cooling and prevents localized overheating. The turbulence column structure not only enhances heat transfer but also regulates the flow field, making the airflow more stable and uniform towards the trailing edge, reducing kinetic energy loss caused by airflow interference.

[0021] Targeted enhancement of trailing edge cooling significantly improves the problem of insufficient trailing edge cooling in traditional cooling technologies by incorporating an array of turbulence columns and a slit structure in the trailing edge region. The turbulence columns increase the heat transfer area and airflow turbulence in the trailing edge region, thereby improving heat transfer efficiency; the slit structure allows the cooling airflow to uniformly cover the trailing edge surface, forming an effective air film protective layer.

[0022] Reducing the amount of cooling air required can be achieved by optimizing the cooling airflow path and improving heat exchange efficiency, thereby reducing the amount of cooling air required while maintaining the same cooling effect, thus improving the overall performance and economy of the engine.

[0023] Extending blade lifespan: Efficient and uniform cooling prevents localized overheating of blades, significantly reducing the risk of deformation, cracking, and ablation caused by thermal stress, thus extending blade lifespan and improving engine reliability. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the overall structure of this utility model.

[0025] Figure 2 This is a three-dimensional structural diagram of the cooling sleeve of this utility model.

[0026] Figure 3 This is a schematic diagram of the planar structure of the cooling sleeve of this utility model.

[0027] Figure 4 This is a schematic diagram of the fixed installation structure of the cooling sleeve of this utility model.

[0028] Figure 5 This is a schematic diagram of the cooling airflow path of this utility model.

[0029] Explanation of reference numerals in the attached figures

[0030] 1. Stator guide vane; 2. Inner cavity; 3. Turbidator column; 4. Slit; 5. Cooling sleeve; 6. Cooling hole; 7. Rib; 8. Shoulder; 9. Sealing weld; 10. Annular gap; 11. Inlet. Detailed Implementation

[0031] The present invention will be further described below by way of embodiments, but the present invention is not limited to the scope of the embodiments described herein.

[0032] like Figures 1-5 As shown, a cooling structure for a gas turbine stator guide vane in an aero-turboshaft engine includes a stator guide vane 1; the stator guide vane 1 is a hollow structure, made of a high-temperature alloy material (such as a nickel-based high-temperature alloy) through investment casting, and has an internal cavity 2. It also includes:

[0033] Cooling sleeve 5, wherein the cooling sleeve 5 is disposed in the inner cavity 2;

[0034] The cooling sleeve 5 has multiple cooling holes 6 at its leading edge, and the cooling holes 6 are close to the leading edge of the stator guide vane 1.

[0035] The upper end of the cooling sleeve 5 is provided with an inlet 11, and an annular shoulder 8 is provided at the inlet 11.

[0036] A slit 4 is provided at the trailing edge of the stator guide vane 1; multiple turbulence columns 3 are provided on the side of the inner cavity 2 near the trailing edge of the stator guide vane 1. The multiple turbulence columns 3 are cast and form an integral array of turbulence columns 3. The array of turbulence columns 3 is preferably arranged in a staggered pattern to increase the heat exchange area and promote airflow turbulence, while ensuring structural strength.

[0037] like Figure 1 As shown, the outer wall of the cooling sleeve 5 and the inner wall of the cavity 2 form an annular gap 10.

[0038] like Figures 1-3 As shown, the multiple cooling holes 6 are evenly divided into four rows, and the four rows of cooling holes 6 are distributed at equal intervals to the front edge of the cooling sleeve 5.

[0039] The number of the slits 4 is multiple, and the multiple slits 4 are respectively aligned with multiple turbulence columns 3. The multiple slits 4 are multiple discrete slit-like holes or continuous elongated holes, the function of which is to allow the cooling airflow to finally flow out through them and form an air film protective layer on the trailing edge surface.

[0040] The cross-section of the inlet 11 is larger than the total area of ​​the plurality of cooling holes 6.

[0041] The cooling sleeve 5 is preferably made of GH3536 (or Hastelloy X) high-temperature alloy. It has good high-temperature strength, oxidation resistance and processability, and is suitable for operation in the cooling environment of the stator guide vane 1.

[0042] Manufacturing process of cooling sleeve 5:

[0043] The cooling sleeve 5 is integrally formed using 3D printing technology. The advantage of this process is that it can precisely manufacture thin-walled, structurally complex parts and eliminates complicated assembly and welding steps.

[0044] The cooling sleeve 5 has a wall thickness of 0.5 mm. This thin-walled design minimizes its volume and mass while ensuring sufficient structural strength and rigidity, providing more space for cooling airflow.

[0045] like Figure 4 As shown, it also includes a positioning mechanism, which consists of four ribs 7 arranged on the side wall of the inner cavity 2.

[0046] The four ribs 7 are attached to the outer wall of the cooling sleeve 5.

[0047] During assembly, the cooling sleeve 5 is inserted into the inner cavity 2 and positioned by the ribs 7. This ensures that the cooling holes 6 on it are aligned with the predetermined impact area on the inner wall of the inner cavity 2 at the leading edge of the stator guide vane 1.

[0048] The shoulder 8 covers and fits onto the upper end face of the inner cavity 2 to seal the upper end of the inner cavity 2.

[0049] like Figure 4 As shown, the shoulder 8 is welded to the upper end of the stator guide vane 1, and a sealing weld 9 is formed at the position where the shoulder 8 contacts the upper end of the stator guide vane 1.

[0050] An annular shoulder 8 is designed at the upper end of the cooling sleeve 5. During assembly, this shoulder 8 contacts the upper end face of the inner cavity 2 of the stator guide vane 1. Subsequently, an argon arc welding process is used to perform self-fusion welding at the contact point between the shoulder 8 and the top of the stator guide vane 1 without adding welding wire, forming a sealing weld 9. This welding method achieves a reliable connection and seal between the cooling sleeve 5 and the stator guide vane 1, ensuring that the cooling airflow will not leak.

[0051] The working process of the cooling structure of the gas turbine stator guide vane 1 is as follows:

[0052] When an aircraft turboshaft engine is operating, the cooling airflow drawn from the compressor follows the following path (e.g. Figure 5 (As indicated by the middle arrow) The cooling process is complete:

[0053] a. Intake and pressurization: The cooling airflow enters the inner cavity 2 of the stator guide vane 1 from the inlet 11 at the upper end of the cooling sleeve 5. Since the cross-section of the inlet 11 is larger than the total area of ​​the subsequent cooling holes 6, the airflow forms a certain cavity pressure in the cooling sleeve 5, providing power for the impinging jet.

[0054] b. Impact cooling: Under the action of cavity pressure, the airflow is ejected at high speed from the four rows of cooling holes 6 opened at the leading edge of the cooling sleeve 5, and impacts the inner wall of the leading edge of the stator guide vane 1 vertically or at a certain angle, so as to achieve efficient impact cooling of the leading edge, the area with the highest heat load.

[0055] c. Convective heat transfer: After the impact, the airflow flows back along the annular gap 10 between the inner wall of the inner cavity 2 and the outer wall of the cooling sleeve 5 towards the trailing edge. During this process, the airflow continuously exchanges heat with the inner wall surface of the stator guide vane 1 via convection.

[0056] d. Turbulence-enhanced heat transfer: When the airflow passes through the array of turbulence columns 3 in the trailing edge region, it is obstructed, divided, and disturbed by the turbulence columns 3, and the flow field becomes extremely turbulent, which greatly enhances the airflow heat transfer efficiency and fully cools the middle and trailing edge regions of the stator guide vane 1.

[0057] e. Final Cooling and Exhaust: Finally, the cooling airflow converges and exits through the slit 4 at the trailing edge to the main combustion gas flow channel. The exhaust airflow not only carries away a large amount of heat but also forms a low-temperature gas film on the outer surface of the trailing edge, separating the high-temperature combustion gas from the metal wall and providing additional gas film cooling protection.

[0058] Through the integrated cooling structure design described above, impact cooling, convection cooling, and slotted cooling are integrated into one, forming a highly efficient, staged cooling path. The cooling airflow first exits from the cooling holes 6 of the cooling sleeve 5, impact cooling the leading edge of the stator guide vane 1; then it flows along the annular gap 10 between the inner wall of the stator guide vane 1 and the outer wall of the cooling sleeve 5 towards the trailing edge for convective heat transfer; finally, it flows through the turbulence column 3 region for further enhanced heat transfer before exiting from the slotted 4 at the trailing edge. This multi-stage synergistic cooling design fully utilizes the cooling potential of the cooling airflow, significantly improving cooling efficiency; it achieves uniform and efficient cooling from the leading edge to the trailing edge, significantly improving the lifespan of the guide vane and the reliability of the engine.

[0059] This utility model is not limited to the above-described embodiments. Any changes in its shape or structure fall within the protection scope of this utility model. The protection scope of this utility model is defined by the appended claims. Those skilled in the art can make various changes or modifications to these embodiments without departing from the principles and essence of this utility model, but all such changes and modifications fall within the protection scope of this utility model.

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