Guide vane platform for a turbine with optimized venting holes

Abstract

A guide vane platform for a turbine, comprising: a plurality of vent holes arranged to direct air from a cavity into the gas path between the turbine blades; wherein the vent holes are located in an area of ​​the gas path with lower static pressure than the interface between the guide vane and the OAS; the vent holes are designed to remove the same amount of air with an area up to five times smaller.

Description

[0001] This invention has been funded by the European Union. However, the views and opinions expressed are solely those of the author(s) and do not necessarily reflect those of the European Union or Clean Aviation. Neither the European Union nor the funding agency can be held responsible for them. Guide vane platform for a turbine with optimized vent holes

[0002] The present invention relates to the field of turbine technology, in particular the design and implementation of vent holes in guide vane platforms for cooling.

[0003] Turbine technology deals with the design and optimization of machines that perform mechanical work by converting energy from a fluid flow. Turbines consist of rotating blades driven by the flow of gas or liquid and are used in various applications such as power generation, aerospace, and industrial processes. Cooling of turbine components is crucial to ensuring the efficiency and service life of the machines.

[0004] In turbine technology, it is important to adequately cool the cavities within the turbine to avoid overheating and component damage. This requires a specific flow volume, which typically enters the gas path at a location downstream of the cavity, where static pressure is lower. The design of the vent holes in the guide vane platforms plays a crucial role in the efficient removal of cooling air.

[0005] Cooling turbine components presents a challenge because the pressure differential between the cavity and the static pressure in the gas path is often small. A large surface area must be provided to remove the required air volume, which can compromise the turbine's design and efficiency. Inadequate air removal can lead to increased cavity pressure and higher leakage upstream of the cavity feed.

[0006] It is known from the state of the art that existing systems for cooling turbine components often require large areas for air extraction to overcome the pressure difference between the cavity and the static pressure in the gas path. These systems are often inefficient and lead to increased cavity pressure and leaks.

[0007] There is therefore a need for a solution that enables efficient air removal from the turbine cavities without requiring large areas. Such a solution should reduce cavity pressure and minimize leakage to improve turbine efficiency and service life.

[0008] According to one aspect of the present invention, a guide vane platform for a turbine comprises a plurality of vent holes arranged to direct air from a cavity into the gas path between the turbine blades; wherein the vent holes are arranged in a region of the gas path with lower static pressure than the interface between the guide vane and the OAS; wherein the vent holes are designed to remove the same amount of air with an area up to five times smaller.

[0009] According to another aspect, the guide vane platform is characterized in that the vent holes are arranged parallel to the motor axis.

[0010] According to a further aspect, the guide vane platform is characterized in that the vent holes can be machined in a single setup by means of electrical discharge machining (EDM).

[0011] According to a further aspect, the guide vane platform is characterized in that the vent holes are arranged at an angle to the motor axis.

[0012] According to a further aspect, the guide vane platform has vent holes with a diameter of less than 5 mm.

[0013] The present invention is explained below by way of example with reference to the accompanying drawings, in which identical reference numerals designate identical or similar components. In the highly schematically simplified figures: Fig. Figure 1 shows a schematic diagram of air flow through vent holes in a turbine vane platform. Fig. 2 shows a guide vane platform with vent holes for discharging air from a cavity into the gas path. Fig. 3 shows a cross-section of the guide vane platform with the arranged vent holes.

[0014] In modern turbines, cavity cooling is a key engineering challenge. These cavities require a specific volume of air to meet their cooling requirements. This air volume typically needs to enter the gas path at a location downstream of the cavity, where static pressure is lower. If the pressure difference between the cavity and the static gas path is small at this location, a large area must be provided to dissipate the required air volume.

[0015] Known systems show an air system designed to cool a turbine's confinement area. This system requires a specific amount of air. The gap (1) provided in the prior art at the connection between the guide vane and the OAS limits air discharge and increases the pressure in the cavity, leading to higher leakage upstream of the cavity inlet.

[0016] The present invention solves the problem described above by introducing vent holes that direct air from a cavity into the gas path between the turbine blades. These vent holes are located in a region (2) of the gas path with lower static pressure than the interface between the guide vane and the OAS. The vent holes are designed to remove the same amount of air with an area up to five times smaller.

[0017] The arrangement of a plurality of vent holes that direct air from a cavity into the gas path between the turbine blades enables efficient cooling of the cavities within the turbine. This helps prevent overheating and damage to the turbine components, increasing the service life and efficiency of the turbine.

[0018] Placing the vent holes in a region (2) of the gas path with lower static pressure than the guide vane-OAS interface (1) enables improved air removal. This reduces the pressure in the cavity and minimizes leakage upstream of the cavity feed, resulting in improved overall turbine performance.

[0019] The design of the vent holes, which allows the same amount of air to be extracted with up to five times less surface area, offers a significant advantage over existing systems. This reduces the need for large areas for air extraction, simplifying the turbine design and increasing its efficiency.

[0020] Arranging the vent holes parallel to the engine axis allows for simpler and more precise hole manufacturing. This reduces the complexity and cost of the manufacturing process, as the holes can be machined in a single setup. Furthermore, the structural integrity of the vane platform is improved, as the holes are evenly and consistently aligned along the engine axis.

[0021] The ability to machine the vent holes in a single setup using electrical discharge machining (EDM) significantly simplifies and accelerates the manufacturing process. This reduces production costs and increases the precision of the holes, as no additional adjustments or repositioning are required. Using EDM allows the holes to be manufactured with high accuracy and surface quality, improving the efficiency and reliability of the vane platform.

[0022] The arrangement of the vent holes at an angle to the motor axis allows for a flexible design of the air discharge paths, facilitating adaptation to specific flow conditions within the turbine. This can lead to improved cooling of the cavities, as the air can be directed specifically to areas with optimal pressure conditions.

[0023] The angled arrangement of the vent holes allows for more efficient airflow control, further reducing cavity pressure and minimizing leaks. This contributes to increasing the overall performance and efficiency of the turbine by optimizing component cooling.

[0024] The ability to position the vent holes at an angle to the engine axis also offers manufacturing advantages, as the holes can be precisely and consistently manufactured in the desired orientation. This improves the structural integrity of the vane platform and reduces the complexity of the manufacturing process.

Claims

[1] A guide vane platform for a turbine, comprising: a plurality of vent holes arranged to direct air from a cavity into the gas path between the turbine blades; wherein the vent holes are arranged in a region of the gas path with lower static pressure than the interface between the guide vane and the OAS; The vent holes are designed to remove the same amount of air with an area up to five times smaller. [2] The guide vane platform according to claim 1, characterized by that the ventilation holes are arranged parallel to the motor axis. [3] The guide vane platform according to any one of the preceding claims, characterized by that the vent holes can be machined in a single setup using electrical discharge machining (EDM). [4] The vane platform according to claim 1 or 3, wherein the vent holes are arranged at an angle to the motor axis. [5] The vane platform according to any one of the preceding claims, wherein the vent holes have a diameter of less than 5 mm.

Images