A cooling channel for improving the cooling performance of a turbine disk shaft

Abstract

The application provides a cooling channel for improving the cooling performance of a turbine disc shaft, a plurality of shaft-inflow channels are arranged in the front half of the shaft, a plurality of shaft-outflow channels are arranged in the rear half of the shaft, an inflow cooling cavity is arranged in the inner part of the connection between the front end surface of the disc and the front half of the shaft, a U-shaped channel is arranged in the disc and the blade, an outflow cooling cavity is arranged in the inner part of the connection between the front end surface of the disc and the front half of the shaft, the shaft-inflow channel, the inflow cooling cavity, the U-shaped channel, the outflow cooling cavity and the shaft-outflow channel are sequentially communicated, an inlet ear-shaped channel is arranged at the connection between the inlet and the shaft-inflow channel, and a disc-in ear-shaped channel is arranged at the connection between the U-shaped channel and the outflow cooling cavity. The application can effectively cool the turbine shaft, the disc and the blade, can better organize the flow in the cooling channel, can improve the backflow of the channel in the disc shaft caused by the rotation centrifugal effect, can reduce the flow loss, and can improve the cooling performance.

Description

Technical Field

[0001] This invention provides a cooling channel to improve the cooling performance of a turbine disk shaft, belonging to the field of turbine technology. Background Technology

[0002] Improvements in aero-engine performance inevitably lead to a significant increase in turbine inlet gas temperature. Studies have shown that for every 55K increase in turbine inlet gas temperature, engine thrust can increase by approximately 10%. However, this increased gas temperature results in a harsher operating environment for turbine components. Besides blade temperatures exceeding material limits, the turbine disk and shaft also experience excessively high temperatures, affecting the overall strength and lifespan of the turbine. Therefore, cooling of all components is essential during turbine operation to ensure its safety.

[0003] For hypersonic vehicles and rockets currently under development, the internal air temperature often exceeds the limits of turbine materials, rendering commonly used film cooling methods unsuitable. Furthermore, to maintain flight speed, the vehicle's weight is limited, preventing the use of a dedicated cooling source for turbine cooling. In such cases, hypersonic vehicles and rockets typically utilize their onboard fuel to cool various components. Given the numerous mechanisms requiring cooling and the limited amount of fuel allocated to the turbine, improving cooling performance is crucial in designing turbine cooling channels.

[0004] Existing research focuses on the cooling of turbine blades, without addressing the cooling requirements of the turbine disk and shaft, or considering the problems that arise when the turbine disk and shaft are cooled using fuel.

[0005] Patent CN105673088B provides a cooling channel for oil-cooled turbine blades. Fuel is pumped into the hollow shaft on the left side of the blade via a fuel pump at the left end. The fuel flows through the cooling channel, passing through the left shaft, disc, blade, disc, and right shaft before exiting. The inlet and outlet of the cooling channel are located on both sides of the shaft, and the corners of the cooling channel are designed at right angles.

[0006] This cooling channel design is overly simplistic, neglecting several issues inherent in turbine cooling. Due to the high turbine speed, the cooling channel experiences rotational effects, resulting in significant backflow within the disc and shaft, leading to high flow resistance. Furthermore, the right-angle bend in the cooling channel design causes substantial fuel separation at the corner, resulting in significant flow losses. The placement of the fuel pump on the left side of the shaft and the fuel outlet on the right side increases the overall model length, consequently increasing the aircraft's weight. Summary of the Invention

[0007] The purpose of this invention is to propose a cooling channel that improves the cooling performance of turbine disk shaft. The cooling channel structure can not only effectively cool the turbine shaft, disk and blades, but also better organize the flow in the cooling channel, improve the backflow caused by the centrifugal force of rotation in the channel of disk shaft, reduce flow loss and improve cooling performance. At the same time, it can also reasonably design the inlet and outlet channels and shorten the model size.

[0008] The main technical means is to arrange the inlet and outlet on the shaft and add ear-shaped cooling channels inside the shaft and wheel.

[0009] The specific technical solution is as follows:

[0010] A cooling channel for improving the cooling performance of a turbine disk shaft has multiple inlets at the front end of the shaft and multiple shaft inflow channels corresponding to the front half of the shaft; and multiple outlets at the rear end of the shaft and multiple shaft outflow channels corresponding to the rear half of the shaft.

[0011] An inflow cooling chamber is provided inside the connection between the front end face of the wheel and the front half of the shaft; a U-shaped channel is provided inside the wheel and the blades; and an outflow cooling chamber is provided inside the connection between the front end face of the wheel and the front half of the shaft.

[0012] The inlet flow channel, inlet cooling chamber, U-shaped channel, outlet cooling chamber, and inlet flow channel are connected in sequence.

[0013] An ear-shaped inlet channel is provided at the connection between the inlet and the internal flow channel; an ear-shaped channel is provided at the connection between the U-shaped channel and the outflow cooling chamber;

[0014] There are four inlets and four outlets; the inlets and outlets are evenly distributed circumferentially along the axis.

[0015] Both the imported human ear-shaped channel and the disc-shaped human ear-shaped channel are curved tubes shaped like the outer contour of a human ear;

[0016] The inlet construction angle α1 of the inlet ear-shaped channel is 75°, and the outlet construction angle β1 is 60°;

[0017] The inlet construction angle α2 of the ear-shaped channel inside the disc is 45°, and the outlet construction angle β2 is 45°.

[0018] The present invention arranges the cooling fuel inlet and outlet on the shaft, so that the fuel storage and recovery device can be arranged between the shafts, which can shorten the length of the entire model and reduce the weight of the hypersonic vehicle.

[0019] To further improve the cooling effect of the turbine shaft and reduce its weight, multiple cooling channels are designed within the shaft. To address the backflow issue within the turbine shaft channels caused by centrifugal force, ear-shaped channel structures are added to areas prone to backflow. Because the structure formed by the ear-shaped channel and the main flow channel is similar to a Tesla valve, it has unidirectional flow capability, significantly increasing the resistance to reverse flow and thus effectively improving backflow.

[0020] Meanwhile, rounded corners are used at the cooling channel corners to ensure a smooth transition and reduce flow losses caused by separation. The inlet uses a contraction channel; according to the principle of flow conservation (ρA1V1=ρA2V2), the channel area decreases, the flow velocity increases, and internal energy is converted into kinetic energy. The temperature of the cooling fuel also decreases to some extent. This ensures better flow of the cooling fuel within the channel and removes more heat, improving cooling performance. The outlet uses an expansion channel; according to the principle of flow conservation, the area increases, the flow velocity decreases, kinetic energy is converted into internal energy, and the fuel temperature also increases to some extent. This helps the cooling fuel recover after flowing out, and the increased temperature ensures more complete combustion when it enters the combustion chamber, releasing more energy.

[0021] Compared with the prior art, the present invention has the following technical effects:

[0022] 1. Regarding the cooling effect, the cooling fuel circulates twice within the turbine disc through the cooling channels, meaning it undergoes two cooling processes. There are four channels within the shaft, which enhances shaft cooling while reducing weight, thus improving the cooling performance of the turbine disc shaft.

[0023] 2. Due to the centrifugal force generated by the high-speed rotation of the turbine, backflow occurs in the cooling channel within the shaft and impeller. An ear-shaped channel was added to the corresponding location in the cooling channel. Since the structure formed by the ear-shaped channel and the main channel is similar to a Tesla valve, it has a unidirectional flow characteristic, preventing reverse flow. Therefore, it effectively improves the backflow phenomenon within the cooling channel, reduces flow resistance, and helps the fuel to better remove heat.

[0024] 3. The inlet is designed as a constricting channel, which can accelerate cooling and facilitate the flow of cooling fuel within the channel and the cooling effect; the outlet is designed as an expanding channel, which can slow down the heating process and help with the recovery and subsequent utilization of cooling fuel.

[0025] 4. All corners within the cooling channel have smooth transitions, which can reduce flow losses caused by separation.

[0026] 5. Placing the inlet and outlet on the axis can shorten the model size. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the cooling fuel flow direction of the present invention;

[0028] Figure 2 This is a schematic diagram of the cooling channel structure of the present invention;

[0029] Figure 3 This is a schematic diagram of the rotor structure of the present invention;

[0030] Figure 4 This is a schematic diagram of the cooling channel structure of the present invention;

[0031] Figure 5 This is a schematic diagram of the angle of the imported human ear-shaped channel of the present invention;

[0032] Figure 6 This is a schematic diagram of the angle of the human ear-shaped channel inside the disc of the present invention. Detailed Implementation

[0033] The specific technical solution of the present invention will be described in conjunction with the accompanying drawings.

[0034] like Figures 1 to 4 As shown, a cooling channel for improving the cooling performance of a turbine disk shaft is provided. The front end of the shaft 1 is provided with four inlets 4, and the front half of the shaft 1 is provided with four shaft inflow channels 5. The rear end of the shaft 1 is provided with four outlets 10, and the rear half of the shaft 1 is provided with four shaft outflow channels 9.

[0035] An inflow cooling chamber 6 is provided inside the connection between the front end face of the wheel 2 and the front half of the shaft 1; a U-shaped channel 7 is provided inside the wheel 2 and the blade 3; and an outflow cooling chamber 8 is provided inside the connection between the front end face of the wheel 2 and the front half of the shaft 1.

[0036] The shaft inlet channel 5, inlet cooling chamber 6, U-shaped channel 7, outlet cooling chamber 8, and shaft outlet channel 9 are connected in sequence;

[0037] An inlet ear-shaped channel 11 is provided at the connection between inlet 4 and the inlet channel 5 inside the shaft; an inlet ear-shaped channel 12 is provided at the connection between U-shaped channel 7 and outlet cooling chamber 8 inside the plate.

[0038] like Figure 1 and Figure 2 As shown: the cooling fuel flows in from the four inlets 4 on the shaft 1. A portion flows into the ear-shaped inlet channel 11, preventing backflow of cooling fuel, and merges with the main flow into the inlet channel 5 inside the shaft. After cooling the left half of the shaft, it enters the inlet cooling chamber 6 inside the impeller 2, and then fully cools the impeller 2 and blades 3 along the U-shaped channel 7 before flowing into the outlet cooling chamber 8. To prevent backflow at the connection between the U-shaped channel 7 and the outlet cooling chamber 8, an ear-shaped channel 12 inside the impeller is arranged at this location. After flowing out of the outlet cooling chamber 8, the cooling fuel enters the outlet channel 9 inside the shaft, cooling the right half of the shaft 1, and then flows out from the four outlets 10.

[0039] Both the imported ear-shaped channel 11 and the inner ear-shaped channel 12 are curved tubes shaped like the outer contour of a human ear;

[0040] like Figure 5 The inlet construction angle α1 of the inlet ear-shaped channel 11 is 75°, and the outlet construction angle β1 is 60°.

[0041] like Figure 6 The inlet construction angle α2 of the ear-shaped channel 12 inside the disc is 45°, and the outlet construction angle β2 is 45°.

[0042] The cross-sectional area of ​​inlet 4 is twice the cross-sectional area of ​​the inlet channel 5 inside the shaft, and the cross-sectional area of ​​outlet 10 is twice the cross-sectional area of ​​the outlet channel 9 inside the shaft.

Claims

1. A cooling channel for improving the cooling performance of a turbine disk shaft, characterized in that, The front end of the shaft (1) is provided with multiple inlets (4), and the front half of the shaft (1) is provided with multiple shaft inflow channels (5); the rear end of the shaft (1) is provided with multiple outlets (10), and the rear half of the shaft (1) is provided with multiple shaft outflow channels (9). An inflow cooling chamber (6) is provided inside the connection between the front end face of the wheel (2) and the front half of the shaft (1); a U-shaped channel (7) is provided inside the wheel (2) and the blade (3); an outflow cooling chamber (8) is provided inside the connection between the rear end face of the wheel (2) and the rear half of the shaft (1). The inlet flow channel (5), inlet cooling chamber (6), U-shaped channel (7), outlet cooling chamber (8), and inlet flow channel (9) are connected in sequence; An inlet ear-shaped channel (11) is provided at the connection between the inlet (4) and the inlet channel (5) inside the shaft; an inlet ear-shaped channel (12) is provided at the connection between the U-shaped channel (7) and the outlet cooling chamber (8). The imported human ear-shaped channel (11) and the disc-shaped human ear-shaped channel (12) are both curved tubes shaped like the outer contour of a human ear; The inlet construction angle α1 of the inlet ear-shaped channel (11) is 75°, and the outlet construction angle β1 is 60°; The inlet construction angle α2 of the ear-shaped channel (12) inside the disc is 45°, and the outlet construction angle β2 is 45°.

2. The cooling channel for improving the cooling performance of a turbine disk shaft according to claim 1, characterized in that, There are four inlets (4) and four outlets (10); the inlets (4) and outlets (10) are evenly arranged along the circumference of the axis (1).

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