Blade sub-cavity air supply structure applied to transition state variable working condition

Abstract

The invention belongs to the technical field of aero-engine turbine disc cavity and blade cooling, and particularly relates to a blade sub-cavity air supply structure applied to transition state variable working conditions, which comprises a turbine disc, a plurality of turbine blades are connected to the circumference of the turbine disc at equal intervals, and a plurality of inner flow channels are formed in the turbine blades; the portions, located on the front edge of the turbine blade and the middle of the blade body, of the inner flow channel communicate with high-pressure heat dissipation flow channels, the portions, located on the tail edge of the turbine blade, of the inner flow channel communicate with low-pressure heat dissipation flow channels, and the high-pressure heat dissipation flow channels and the low-pressure heat dissipation flow channels are arranged in the turbine disc and do not interfere with each other. During use, reasonable distribution of blade cooling air flow can be achieved by arranging the high-pressure heat dissipation flow channels and the low-pressure heat dissipation flow channels, the use amount of blade cooling air is remarkably reduced while the thermal protection capacity of a turbine disc and blades is not affected under the transition state variable working condition, and the turbine blade has the advantages of being simple in structure, convenient to machine, obvious in effect and the like. The cooling device can be applied to cooling schemes of various turbine discs and blades.

Description

Technical Field

[0001] This invention belongs to the field of turbine disk cavity and blade cooling technology for aero-engines, and particularly relates to a blade cavity air supply structure applied to transitional variable operating conditions. Background Technology

[0002] Aero engines are the power heart of the modern aviation industry and are hailed as the "jewel in the crown of industry." Currently, the turbine inlet temperature of aero engines has exceeded 2100K, while the highest allowable temperature of the current third-generation single-crystal high-temperature alloy is 1370K. Even if the temperature resistance of high-temperature alloys is expected to be improved to 1423K and protected by thermal barrier coatings, there is still a temperature difference of about 600K that needs to be achieved through efficient cooling technology.

[0003] Generally speaking, the greater the airflow rate, the better the cooling effect on hot-end components. The proportion of cool air (including seals) in the high-pressure rotor components of turbofan aero-engines is typically 6% to 10%. This proportion generally increases further as the turbine inlet temperature rises. However, the airflow rate of an aero-engine is limited; excessive cool air consumption leads to a decrease in engine thrust and overall efficiency. Therefore, achieving thermal protection for hot-end components with minimal cool air consumption and ensuring their long-term reliable operation is a pressing technical problem that needs to be solved.

[0004] Therefore, we propose a blade chamber air supply structure applicable to transitional variable operating conditions. Summary of the Invention

[0005] The purpose of this invention is to provide a blade chamber air supply structure applicable to transitional variable operating conditions, in order to solve the above-mentioned problems.

[0006] To achieve the above objectives, the present invention provides the following solution:

[0007] A blade-cavity air supply structure for use in transitional operating conditions includes a turbine disk with a plurality of turbine blades circumferentially and at equal intervals. Each turbine blade has a plurality of internal flow channels. The internal flow channels located at the leading edge and middle of the turbine blade are connected to a high-pressure cooling channel, and the internal flow channels located at the trailing edge of the turbine blade are connected to a low-pressure cooling channel. The high-pressure and low-pressure cooling channels are disposed within the turbine disk and do not interfere with each other.

[0008] Optionally, the outer edge of the turbine disk is provided with a plurality of turbine disk tenons at equal intervals in the circumferential direction, and turbine blade tenons are connected in the turbine disk tenons, and the turbine blades are fixed to the turbine blade tenons.

[0009] One side of the turbine disk is connected to a pre-rotation air supply structure, and the other side of the turbine disk is connected to a turbine disk rear retaining ring.

[0010] A compartmentalized air supply baffle is fixedly connected to the middle of the turbine disk tenon groove;

[0011] The pre-swirl air supply structure, the chambered air supply baffle, the inner wall of the turbine disk tenon groove, and the inner wall of the turbine blade tenon together form a high-pressure air chamber;

[0012] The turbine disk rear retaining ring, the chambered air supply baffle, the inner wall of the turbine disk tenon groove, and the inner wall of the turbine blade tenon together form a low-pressure air chamber;

[0013] The turbine blade tenon has a turbine blade inlet chamber and a turbine blade rear inlet chamber that do not interfere with each other. The turbine blade inlet chamber is connected to the high-pressure chamber, and the turbine blade rear inlet chamber is connected to the low-pressure chamber.

[0014] The pre-swirl air supply structure, the high-pressure air chamber, the turbine blade inlet air chamber, and the inner flow channel located at the leading edge and middle of the turbine blade are sequentially connected to form the high-pressure heat dissipation flow channel;

[0015] The turbine disk, the low-pressure air chamber, the rear air inlet chamber of the turbine blade, and the inner flow channel located at the trailing edge of the turbine blade are sequentially connected to form the low-pressure heat dissipation flow channel.

[0016] Optionally, the pre-swirl air supply structure includes a plurality of air supply holes that are configured and connected to the high-pressure air chamber in a one-to-one correspondence.

[0017] The high-pressure cooling airflow enters the inner flow channel located at the leading edge of the turbine blade and the middle of the blade body through the high-pressure heat dissipation channel formed by the air supply hole of the pre-swirl air supply structure, the high-pressure air chamber and the turbine blade inlet air chamber arranged in sequence.

[0018] Optionally, a low-pressure air chamber is provided inside the turbine disk, the air inlet of the low-pressure air chamber is located on one side of the axis of the turbine disk, and the low-pressure air chamber is connected to several low-pressure air chambers.

[0019] The low-pressure cooling airflow enters the inner flow channel located at the trailing edge of the turbine blade through the low-pressure heat dissipation channel formed by the low-pressure air chamber, the low-pressure air cavity, and the rear air inlet cavity of the turbine blade in sequence.

[0020] Optionally, the turbine blade tenon and the turbine disk tenon are fixed together by a mortise and tenon joint.

[0021] Optionally, the turbine disk has a plurality of turbine disk air supply chambers, and the plurality of turbine disk air supply chambers correspond one-to-one with the plurality of low-pressure air chambers. One end of the turbine disk air supply chamber is connected to the low-pressure air chamber, and the other end of the turbine disk air supply chamber is connected to the low-pressure air chamber.

[0022] Optionally, the air outlet of the air supply hole has a rectangular structure, and the air inlet of the air supply hole is provided with a flow guiding structure.

[0023] Optionally, the turbine blade inlet chamber has a racetrack-shaped structure.

[0024] Optionally, both the pre-swirl air supply structure and the turbine disk rear retaining ring are fixed to the turbine disk by bolts.

[0025] Optionally, the thickness of the chambered air supply baffle is 2-3mm and the height is 2.5-3.5mm, and the distance between the chambered air supply baffle and the turbine disk tenon groove near the turbine disk rear retaining ring is 18-25mm.

[0026] Compared with the prior art, the present invention has the following advantages and technical effects:

[0027] In use, this invention can achieve a reasonable distribution of cooling airflow for the blades by setting high-pressure cooling channels and low-pressure cooling channels. Under transitional operating conditions, it can significantly reduce the amount of cooling air used for the blades without affecting the thermal protection capability of the turbine disk and blades. It also features simple structure, convenient processing, and obvious effect, and can be applied to various cooling schemes for turbine disks and blades. Attached Figure Description

[0028] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the embodiments will be briefly described below. Obviously, the drawings described below are only some embodiments of the present invention. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0029] Figure 1 This is a schematic diagram of the structure of the present invention;

[0030] Figure 2 This is an exploded view of the structure of the present invention;

[0031] Figure 3 This is a schematic diagram of the turbine blade tenon structure of the present invention;

[0032] Figure 4 This is a schematic diagram of the turbine disk structure of the present invention;

[0033] Figure 5 For the present invention Figure 4 Enlarged view of a portion of point A in the middle;

[0034] Figure 6 This is a schematic diagram of the turbine disk rear retaining ring structure of the present invention;

[0035] Figure 7 This is a first-view structural schematic diagram of the pre-spinning gas supply structure of the present invention;

[0036] Figure 8 This is a second-view structural schematic diagram of the pre-spinning gas supply structure of the present invention;

[0037] Figure 9 For the present invention Figure 7 Enlarged view of a section at point B in the middle;

[0038] Figure 10 For the present invention Figure 8 Enlarged view of a section at point C;

[0039] Figure 11 It is the fluid mesh model used for performing numerical calculations;

[0040] Figure 12 It is the percentage of cooling air flow rate under different operating conditions in the implementation example;

[0041] Among them, 1. Turbine blade tenon; 2. Turbine blade inlet chamber; 3. Turbine blade rear inlet chamber; 4. Turbine disk tenon groove; 5. Turbine disk air supply chamber; 6. Chambered air supply baffle; 7. Pre-swirl air supply structure; 8. Turbine disk rear retaining ring. Detailed Implementation

[0042] The technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, and not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0043] To make the above-mentioned objects, features and advantages of the present invention more apparent and understandable, the present invention will be further described in detail below with reference to the accompanying drawings and specific embodiments.

[0044] Reference Figures 1 to 8 This invention discloses a blade cavity air supply structure for use in transitional operating conditions, including a turbine disk, a number of turbine blades connected at equal intervals around the turbine disk, and a number of internal flow channels opened inside the turbine blades. The internal flow channels located at the leading edge and middle of the blade body are connected to a high-pressure heat dissipation channel, and the internal flow channel located at the trailing edge of the turbine blade is connected to a low-pressure heat dissipation channel. The high-pressure heat dissipation channel and the low-pressure heat dissipation channel are arranged inside the turbine disk, and the high-pressure heat dissipation channel and the low-pressure heat dissipation channel do not interfere with each other.

[0045] In use, this invention can achieve a reasonable distribution of cooling airflow for the blades by setting high-pressure cooling channels and low-pressure cooling channels. Under transitional operating conditions, it can significantly reduce the amount of cooling air used for the blades without affecting the thermal protection capability of the turbine disk and blades. It also features simple structure, convenient processing, and obvious effect, and can be applied to various cooling schemes for turbine disks and blades.

[0046] As an optional implementation, a plurality of turbine disk tenons 4 are provided at equal intervals around the outer edge of the turbine disk, and turbine blade tenons 1 are connected in the turbine disk tenons 4, with the turbine blades fixed on the turbine blade tenons 1.

[0047] One side of the turbine disk is connected to a pre-swivel air supply structure 7, and the other side of the turbine disk is connected to a turbine disk rear retaining ring 8.

[0048] A compartmentalized air supply baffle 6 is fixedly connected to the middle of the turbine disk tenon groove 4;

[0049] The pre-rotating air supply structure 7, the chambered air supply baffle 6, the inner wall of the turbine disk tenon groove 4 and the inner wall of the turbine blade tenon 1 together form a high-pressure air chamber.

[0050] The turbine disk rear retaining ring 8, the chamber supply baffle 6, the inner wall of the turbine disk tenon groove 4 and the inner wall of the turbine blade tenon 1 together form a low-pressure air chamber.

[0051] The turbine blade tenon 1 has a turbine blade inlet chamber 2 and a turbine blade rear inlet chamber 3 that do not interfere with each other. The turbine blade inlet chamber 2 is connected to the high-pressure chamber, and the turbine blade rear inlet chamber 3 is connected to the low-pressure chamber.

[0052] The pre-swirl air supply structure 7, the high-pressure air chamber, the turbine blade inlet air chamber 2, and the inner flow channel located at the leading edge of the turbine blade and the middle of the blade body are connected in sequence to form a high-pressure heat dissipation flow channel.

[0053] The turbine disk, low-pressure air chamber, turbine blade rear air inlet 3, and inner flow channel located at the trailing edge of the turbine blade are connected in sequence to form a low-pressure heat dissipation flow channel.

[0054] The present invention includes a turbine blade tenon 1, a turbine blade inlet air chamber 2, a turbine blade rear air chamber 3, a turbine disk tenon groove 4, a turbine disk air supply chamber 5, a chambered air supply baffle 6, a pre-swirl air supply structure 7, and a turbine disk rear retaining ring 8.

[0055] The turbine blade tenon 1 is fitted with the turbine disk tenon 4 to fix the radial and circumferential positions of the turbine blade, and can withstand a large radial load. One stream of cold air passes through the pre-swirl supply structure 7 and flows into the inner flow channel of the leading edge and middle of the blade through the turbine blade inlet chamber 2, and flows out through the film gas holes arranged on the blade surface to form a film gas cover. Another stream of cold air passes through the inner side of the turbine disk, the low-pressure chamber, and the turbine disk supply chamber 5, and then enters the inner flow channel of the blade trailing edge through the turbine blade rear inlet chamber 3, and flows out through the blade trailing edge slit. The chamber-separated supply baffle 6 is located in the turbine disk tenon 4 to separate the two streams of cooling air and prevent the mixing of the two streams of cooling air with different pressures and temperatures. The turbine disk rear retaining ring 8 is fixed to the rear side of the turbine disk to prevent the leakage of cold air flowing out of the turbine disk supply chamber 5, and together with the pre-swirl supply structure 7, determines the axial position of the turbine blade.

[0056] Furthermore, the bottom radius of the turbine disk tenon 4 is between 150-155mm, the top radius of the turbine disk tenon 4 is between 172-180mm, and the total number of tenons on the entire turbine disk is 51. The turbine disk air supply chamber 5 has a cylindrical structure with a radius between 2mm and 3mm.

[0057] The inner diameter of the turbine disc rear retaining ring 8 is between 145-150mm, the outer diameter is between 155-165mm, and the thickness is 2-4mm.

[0058] As an optional implementation, the pre-swirl air supply structure 7 includes several air supply holes that are configured and connected to the high-pressure air chambers one by one.

[0059] The high-pressure cooling airflow enters the inner flow channel located at the leading edge of the turbine blade and the middle of the blade body through the high-pressure heat dissipation channel formed by the air supply hole, high-pressure air chamber and turbine blade inlet air chamber 2 arranged sequentially along the pre-swirl air supply structure 7.

[0060] The pre-rotating air supply structure 7 has 51 air supply holes, and the outlet end of each air supply hole is rectangular with an area of ​​60-70 mm². 2 .

[0061] As an optional implementation, a low-pressure air chamber is provided inside the turbine disk, with the air inlet of the low-pressure air chamber located on one side of the turbine disk's shaft, and the low-pressure air chamber is connected to several low-pressure air chambers.

[0062] The low-pressure cooling airflow enters the inner flow channel located at the trailing edge of the turbine blade through the low-pressure air chamber, the low-pressure air cavity, and the turbine blade rear air inlet 3, which are arranged sequentially.

[0063] As an optional implementation, the turbine blade tenon 1 and the turbine disk tenon 4 are fixed together by mortise and tenon joint.

[0064] As an optional implementation, the turbine disk has a plurality of turbine disk air supply chambers 5, which correspond one-to-one with a plurality of low-pressure air chambers. One end of the turbine disk air supply chamber 5 is connected to the low-pressure air chamber, and the other end of the turbine disk air supply chamber 5 is connected to the low-pressure air chamber.

[0065] As an optional implementation, the air outlet of the air supply hole has a rectangular structure, and the air inlet of the air supply hole is provided with a flow guiding structure.

[0066] See the air guide structure at the air inlet end of the air supply port. Figure 9 See the air outlet end of the air supply port. Figure 10 .

[0067] As an optional implementation, the turbine blade inlet chamber 2 has a racetrack-shaped structure.

[0068] The turbine blade's inlet chamber 2 has a racetrack-shaped structure. The radius of the two semicircles is 1-1.5mm, and the length of the rectangular part in the middle is 8-12mm. The turbine blade's rear inlet chamber also has a racetrack-shaped shape, with the radius of the two semicircles being 1-1.5mm and the length of the rectangular part in the middle being 2-5mm.

[0069] As an optional implementation, both the pre-swirl air supply structure 7 and the turbine disk rear retaining ring 8 are fixed to the turbine disk by bolts.

[0070] As an optional implementation, the chamber air supply baffle 6 has a thickness of 2-3mm and a height of 2.5-3.5mm, and the distance between the chamber air supply baffle 6 and the turbine disk tenon groove 4 near the turbine disk rear retaining ring 8 is 18-25mm.

[0071] The thickness of the chambered air supply baffle 6 is 2-3mm, the height is 2.5-3.5mm, and the distance between the chambered air supply baffle 6 and the front side of the turbine disk tenon groove is between 18-25mm.

[0072] The optimization effect of the compartmentalized air supply structure and installation method on reducing the amount of cooling air under varying operating conditions was verified by using a one-dimensional fluid mesh calculation method.

[0073] In this application example, the bottom radius of the turbine disk tenon 4 is 152 mm, the top radius of the turbine disk tenon 4 is 172 mm, the radius of the turbine disk air supply chamber 5 is 2 mm, and the total number of tenons in the entire ring is 51. The pre-rotating air supply structure 7 has 51 air supply holes, which are rectangular in shape and have an area of ​​62 mm². 2 The turbine blade inlet chamber 2 is racetrack-shaped, with the radius of the two semicircles being 1mm and the length of the central rectangular section being 10mm. The turbine blade rear inlet chamber 3 is also racetrack-shaped, with the radius of the two semicircles being 1mm and the length of the central rectangular section being 3mm. The chamber-splitting air supply baffle 6 has a thickness of 2mm and a height of 2.5mm. The distance between the chamber-splitting air supply baffle 6 and the side of the turbine disk tenon groove 4 closest to the pre-swirl air supply structure 7 is 20mm. The turbine disk rear retaining ring 8 has an inner diameter of 148mm, an outer diameter of 155mm, and a thickness of 2mm.

[0074] Under the same computational boundary conditions, compared with the cooling volume using a traditional single-chamber air supply structure, the cooling volume using a multi-chamber air supply structure decreased by 5.1%, 5.2%, 5.1%, and 8.4% under different operating conditions.

[0075] In the description of this invention, it should be understood that the terms "longitudinal", "lateral", "up", "down", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings, and are only for the convenience of describing this invention, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of this invention.

[0076] The embodiments described above are merely preferred embodiments of the present invention and are not intended to limit the scope of the present invention. Various modifications and improvements made by those skilled in the art to the technical solutions of the present invention without departing from the spirit of the present invention should fall within the protection scope defined by the claims of the present invention.

Claims

1. A blade-type chambered air supply structure for use in transitional variable operating conditions, comprising a turbine disk, wherein a plurality of turbine blades are circumferentially and equally spaced, and a plurality of internal flow channels are formed within the turbine blades, characterized in that, The inner flow channel located at the leading edge and middle of the turbine blade is connected to a high-pressure heat dissipation channel, and the inner flow channel located at the trailing edge of the turbine blade is connected to a low-pressure heat dissipation channel. The high-pressure heat dissipation channel and the low-pressure heat dissipation channel are arranged inside the turbine disk, and the high-pressure heat dissipation channel and the low-pressure heat dissipation channel do not interfere with each other.

2. The blade chamber air supply structure applied to transitional variable operating conditions according to claim 1, characterized in that: The outer edge of the turbine disk is provided with a plurality of turbine disk tenons (4) at equal intervals in the circumference. Turbine blade tenons (1) are connected in the turbine disk tenons (4), and the turbine blades are fixed on the turbine blade tenons (1). One side of the turbine disk is connected to a pre-rotation air supply structure (7), and the other side of the turbine disk is connected to a turbine disk rear retaining ring (8). A chambered air supply baffle (6) is fixedly connected to the middle of the turbine disk tenon groove (4); The pre-swirl air supply structure (7), the chambered air supply baffle (6), the inner wall of the turbine disk tenon groove (4) and the inner wall of the turbine blade tenon (1) together form a high-pressure air chamber; The turbine disk rear retaining ring (8), the chamber supply baffle (6), the inner wall of the turbine disk tenon groove (4) and the inner wall of the turbine blade tenon (1) together form a low-pressure air chamber; The turbine blade tenon (1) has a turbine blade inlet air chamber (2) and a turbine blade rear air chamber (3) that do not interfere with each other. The turbine blade inlet air chamber (2) is connected to the high-pressure air chamber, and the turbine blade rear air chamber (3) is connected to the low-pressure air chamber. The pre-swirl air supply structure (7), the high-pressure air chamber, the turbine blade inlet air chamber (2), and the inner flow channel located at the leading edge and middle of the turbine blade are sequentially connected to form the high-pressure heat dissipation flow channel; The turbine disk, the low-pressure air chamber, the rear air inlet chamber (3) of the turbine blade, and the inner flow channel located at the trailing edge of the turbine blade are sequentially connected to form the low-pressure heat dissipation flow channel.

3. The blade chamber air supply structure for transitional variable operating conditions according to claim 2, characterized in that: The pre-rotating air supply structure (7) includes several air supply holes that are configured and connected to the high-pressure air chambers one by one. The high-pressure cooling airflow enters the inner flow channel located at the leading edge of the turbine blade and the middle of the blade body through the high-pressure heat dissipation channel formed by the air supply hole of the pre-swirl air supply structure (7), the high-pressure air chamber and the turbine blade inlet air chamber (2) arranged in sequence.

4. The blade chamber air supply structure applied to transitional variable operating conditions according to claim 2, characterized in that: A low-pressure air chamber is provided inside the turbine disk, and the air inlet of the low-pressure air chamber is located on one side of the axis of the turbine disk. The low-pressure air chamber is connected to several low-pressure air cavities. The low-pressure cooling airflow enters the inner flow channel located at the trailing edge of the turbine blade through the low-pressure heat dissipation channel formed by the low-pressure air chamber, the low-pressure air cavity and the turbine blade rear air inlet cavity (3) arranged in sequence.

5. The blade chamber air supply structure for transitional variable operating conditions according to claim 2, characterized in that: The turbine blade tenon (1) and the turbine disk tenon (4) are fixed together by mortise and tenon joint.

6. The blade chamber air supply structure for transitional variable operating conditions according to claim 4, characterized in that: The turbine disk has a plurality of turbine disk air supply chambers (5), and the plurality of turbine disk air supply chambers (5) correspond one-to-one with the plurality of low-pressure air chambers. One end of the turbine disk air supply chamber (5) is connected to the low-pressure air chamber, and the other end of the turbine disk air supply chamber (5) is connected to the low-pressure air chamber.

7. The blade chamber air supply structure for use in transitional variable operating conditions according to claim 3, characterized in that: The air outlet of the air supply hole has a rectangular structure, and the air inlet of the air supply hole is provided with a flow guide structure.

8. The blade chamber air supply structure for transitional variable operating conditions according to claim 2, characterized in that: The turbine blade inlet chamber (2) has a racetrack-shaped structure.

9. A blade chamber-type air supply structure for use in transitional variable operating conditions according to claim 2, characterized in that: The pre-swirl air supply structure (7) and the turbine disk rear retaining ring (8) are both fixed to the turbine disk by bolts.

10. A blade chamber-type air supply structure for use in transitional variable operating conditions according to claim 2, characterized in that: The thickness of the chamber air supply baffle (6) is 2-3mm and the height is 2.5-3.5mm. The distance between the chamber air supply baffle (6) and the turbine disk tenon groove (4) near the turbine disk rear retaining ring (8) is 18-25mm.

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