A pre-swirl plenum canted seal lip structure

Abstract

The application discloses a pre-rotation pressurization inclined seal lip structure and relates to the technical field of turbine of high-temperature components of an aero-engine. The application solves the problems of disturbing the main flow gas, wasting the aerodynamic performance of the blade and backflow of the gas in the prior art. The end of the rotor rim of the rotor towards the stator is provided with an L-shaped protrusion, and the end of the stator rim of the stator towards the rotor is provided with an L-shaped groove; a gas flow channel is arranged between the L-shaped protrusion and the L-shaped groove, and the outlet of the gas flow channel is towards the blade root position of the turbine moving blade. The application modifies the structure of the axial gap at the rotor-stator rim of the turbine, guides and pressurizes the sealing gas to a certain extent, reduces the circumferential velocity difference and the flow angle difference between the sealing gas and the main flow gas, increases the outlet pressure of the sealing gas, reduces the backflow phenomenon of the gas, and simultaneously can cool the blade root to a certain extent.

Description

Technical Field

[0001] This invention relates to the field of turbine technology for high-temperature components of aero engines, specifically a pre-swirl pressurization tilting sealing lip structure. Background Technology

[0002] An aero-engine turbine consists of stationary and rotating components. The turbine guide vane is the stationary component, while the turbine rotor is the rotating component, both of which are in direct contact with the high-temperature mainstream combustion gases. An axial clearance inevitably exists between the rotating and stationary components, and an annular cavity, called the turbine disk cavity, exists between the two. To prevent the high-temperature combustion gases in the mainstream channel from flowing back into the turbine disk cavity, high-pressure, low-temperature gas is drawn from the compressor and introduced into the turbine disk cavity as a sealing gas. This gas is then discharged into the mainstream channel through the sealing lip. This process protects the turbine disk from the high-temperature corrosion of the combustion gases and also provides film cooling to the turbine blade roots and lower endwalls.

[0003] The introduction of sealing gas can cool and protect the turbine disk cavity and blade roots, but it also affects the flow pattern of the mainstream gas. The circumferential velocity difference and flow angle difference between the sealing outflow and the mainstream gas will generate viscous shear, disrupting the flow pattern of the mainstream gas and thus reducing the aerodynamic performance of the turbine. The relative motion between the stationary and moving blades will cause uneven circumferential pressure distribution, resulting in the local mainstream gas pressure at the turbine rim being greater than the sealing gas pressure inside the turbine disk cavity, causing gas backflow.

[0004] A series of problems, such as sealing gas disrupting the mainstream gas flow, damaging blade aerodynamic performance, and gas backflow, affect the overall efficiency and service life of aero engines. Solving these problems is of great significance. Summary of the Invention

[0005] To address the problems mentioned above in existing technologies, such as sealing gas disrupting the mainstream gas flow, impairing blade aerodynamic performance, and causing gas backflow, this invention proposes a pre-swirl-boosting tilted sealing lip structure. This invention modifies the axial clearance at the turbine rotor-stator rim to guide, redirect, and boost the sealing gas, reducing the circumferential velocity and flow angle differences between the sealing gas and the mainstream gas, increasing the sealing gas outlet pressure, reducing gas backflow, and simultaneously providing some cooling to the blade root.

[0006] This invention proposes a pre-swirl booster tilting sealing lip structure, which specifically includes a stator, a rotor, a turbine shaft, and a main flow channel. The stator and rotor are arranged in the main flow channel, and the rotor is mounted on the turbine shaft. The rotor rim facing the stator has an L-shaped protrusion, and the stator rim facing the rotor has an L-shaped groove. A gas flow channel is arranged between the L-shaped protrusion and the L-shaped groove, and the outlet of the gas flow channel faces the root of the turbine blade.

[0007] Furthermore, the angle between the long side of the L-shaped groove and the turbine shaft axis is 25 degrees.

[0008] Furthermore, the L-shaped groove is provided with a plurality of gradually expanding twisted grooves, which are arranged along the stacking curve, and the cross-sectional area of ​​the gradually expanding twisted grooves gradually increases from the starting point to the ending point of the stacking curve.

[0009] Furthermore, the stacked curve is twisted in the circumferential direction.

[0010] Furthermore, the angle between the tangent at the endpoint of the stacked curve and the circumferential direction is 44 degrees.

[0011] Furthermore, the cross-sectional shape of the gradually expanding twisted groove is rectangular.

[0012] Furthermore, the number of the gradually expanding twisted grooves is an integer multiple of the number of turbine blades.

[0013] The beneficial effects of the pre-spinning pressurized inclined sealing lip structure described in this invention are as follows:

[0014] (1) The pre-swirl pressurized inclined sealing lip structure of the present invention solves the problems of sealing gas disturbing the mainstream gas, losing the aerodynamic performance of the blade, and backflow of gas in the prior art. The lip structure is composed of the turbine-stator wheel rim. By modifying the axial clearance at the turbine-stator wheel rim, the sealing gas is guided, steered and pressurized to a certain extent, reducing the circumferential velocity difference and flow angle difference between the sealing gas and the mainstream gas, increasing the sealing gas outlet pressure, reducing the backflow of gas, and also playing a certain cooling role at the blade root.

[0015] (2) The pre-swirl boosting inclined sealing lip structure of the present invention, through the setting of the gradually expanding torsional groove, makes the sealing gas have a certain circumferential angle when entering the mainstream channel, producing a pre-swirl effect, which weakens the viscous shear resistance of the sealing gas on the mainstream gas, and has a smaller impact on the dynamic performance of the turbine blade; the gradual increase of the cross-sectional area of ​​the gradually expanding torsional groove can decelerate and boost the sealing gas. Attached Figure Description

[0016] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an improper limitation of the invention.

[0017] In the attached diagram:

[0018] Figure 1 This is a schematic diagram of a pre-spinning pressurized inclined sealing lip structure according to the present invention;

[0019] Figure 2 This is a schematic diagram of the turbine stator rim portion of a pre-spinning pressurized inclined sealing lip structure according to the present invention;

[0020] Figure 3 This is a schematic diagram of the gradually expanding torsion groove of the pre-rotating pressurized inclined sealing lip structure described in this invention;

[0021] Figure 4 This is a schematic diagram of the turbine rotor rim portion of a pre-spinning pressurized inclined sealing lip structure according to the present invention;

[0022] Wherein: 1-Stator rim, 2-Rotor rim, 3-Turbine shaft, 4-Turbine rotor, 5-L-shaped groove, 6-Gradually expanding twisted groove, 7-Accumulated curve, 8-Accumulated curve endpoint, 9-Main channel, 10-L-shaped protrusion, 11-Turbine blade. Detailed Implementation

[0023] The technical solution of this invention will now be clearly and completely described with reference to the accompanying drawings. Obviously, the described embodiments are only a part of, and not all, of the embodiments of this invention. All other embodiments obtained by those skilled in the art based on the embodiments of this invention without inventive effort are within the scope of protection of this invention.

[0024] In the description of this invention, it should be noted that the terms "center," "upper," "lower," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and for simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention. Furthermore, the terms "first," "second," and "third" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0025] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.

[0026] Furthermore, the technical features involved in the different embodiments of the present invention described below can be combined with each other as long as they do not conflict with each other.

[0027] Specific implementation method one: See Figures 1-4 This embodiment is described in detail. The pre-swirl booster tilted sealing lip structure described in this embodiment specifically includes a stator, a rotor, a turbine shaft 3, and a main channel 9. The stator and rotor are disposed within the main channel 9, with the rotor mounted on the turbine shaft 3. The rotor includes a turbine rotor 4, a rotor rim 2, and several turbine blades 11. The turbine rotor 4 is mounted on the turbine shaft 3, and the outer ring of the turbine rotor 4 is provided with a rotor rim 2, on which several turbine blades 11 are disposed. The sealing lip structure is jointly formed by the stator rim 1 and the rotor rim 2 of the turbine, constituting a slit structure. An L-shaped protrusion 10 is provided at the end of the rotor rim 2 facing the stator, and an L-shaped groove 5 is provided at the end of the stator rim 1 facing the rotor. The long side of the L-shaped protrusion 10 is parallel to the long side of the L-shaped groove 5. The L-shaped groove 5 is tilted, with its opening facing the axis of the turbine shaft 3 and the turbine rotor 4. The angle between the long side of the L-shaped groove 5 and the axis of the turbine shaft 3 is 25 degrees. Figure 1 As shown, a gas flow channel is provided between the L-shaped protrusion 10 and the L-shaped groove 5, with the outlet of the gas flow channel facing the root of the turbine blade 11. The sealing gas flows in from the minimum radius of the sealing lip structure and enters the flow channel formed by the L-shaped groove 5 and the L-shaped protrusion 10. This causes the sealing gas to be ejected towards the root of the downstream turbine blade 11 when it flows into the mainstream channel, cooling the root of the turbine blade 11 and reducing the flow angle difference between the sealing gas and the mainstream gas.

[0028] The L-shaped groove 5 is provided with several gradually expanding twisted grooves 6, which are arranged along an accumulation curve 7. The accumulation curve 7 is an arc defined by three points. By modifying the positions of the three points, the degree of twist can be modified, thereby changing the accumulation path of the gradually expanding twisted grooves 6. The cross-sectional area of ​​the gradually expanding twisted grooves 6 gradually increases from the starting point 8 of the accumulation curve 7 to the ending point 8, thus gradually expanding the flow area. Figure 3 As shown.

[0029] The accumulation curve 7 is twisted in the circumferential direction, and the tangent at the end point 8 of the accumulation curve makes an angle of 44 degrees with the circumferential direction. This is to reverse the flow direction of the sealing gas outlet, so that the sealing gas has a certain circumferential angle when it enters the mainstream channel 9, producing a pre-swirl effect, weakening the viscous shear resistance of the sealing gas on the mainstream gas, and having a smaller impact on the dynamic performance of the turbine blades.

[0030] The cross-sectional shape of the gradually expanding twisted groove 6 is rectangular or other shapes.

[0031] The number of the gradually expanding twisted grooves 6 is an integer multiple of the number of turbine blades 11; specifically, the number of the gradually expanding twisted grooves 6 is twice the number of turbine blades 11, the number of turbine blades 11 is 53, and the number of the gradually expanding twisted grooves 6 is 106.

[0032] In summary, the pre-swirl-boosting tilted sealing lip structure of this invention solves the problems of sealing gas disturbing the mainstream gas, damaging blade aerodynamic performance, and causing backflow of combustion gas in the prior art. The lip structure is composed of the rim of the turbine rotor and stator. By modifying the axial clearance at the turbine rotor and stator rims, it guides and boosts the sealing gas, reducing the circumferential velocity difference and flow angle difference between the sealing gas and the mainstream gas, increasing the sealing gas outlet pressure, reducing backflow of combustion gas, and simultaneously providing some cooling to the blade root. The pre-swirl-boosting tilted sealing lip structure of this invention, through the gradually expanding torsional groove 6, ensures that the sealing gas has a certain circumferential angle when entering the mainstream channel, producing a pre-swirl effect. This weakens the viscous shear resistance of the sealing gas on the mainstream gas, resulting in a smaller impact on the turbine blade's dynamic performance. The gradually increasing cross-sectional area of ​​the gradually expanding torsional groove can decelerate and boost the sealing gas.

[0033] The specific embodiments described above further illustrate the purpose, technical solution, and beneficial effects of the present invention. It should be understood that the above descriptions are merely specific embodiments of the present invention and are not intended to limit the invention. They can also be reasonable combinations of the features described in the above embodiments. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A pre-rotating pressurized inclined sealing lip structure, characterized in that: The system includes a stator, a rotor, a turbine shaft (3), and a main channel (9). The stator and rotor are housed in the main channel (9), and the rotor is mounted on the turbine shaft (3). An L-shaped protrusion (10) is provided at the end of the rotor rim (2) facing the stator, and an L-shaped groove (5) is provided at the end of the stator rim (1) facing the rotor. A gas flow channel is provided between the L-shaped protrusion (10) and the L-shaped groove (5), and the outlet of the gas flow channel faces the root of the turbine blade (11). Several gradually expanding twisted grooves (6) are provided on the L-shaped groove (5). The gradually expanding twisted grooves (6) are provided along the stacking curve (7), and the cross-sectional area of ​​the gradually expanding twisted grooves (6) gradually increases from the starting point of the stacking curve (7) to the ending point (8) of the stacking curve. The stacked curve (7) is twisted in the circumferential direction; the angle between the tangent at the end point (8) of the stacked curve and the circumferential direction is 44 degrees.

2. The pre-spinning pressurized inclined sealing lip structure according to claim 1, characterized in that: The angle between the long side of the L-shaped groove (5) and the axis of the turbine shaft (3) is 25 degrees.

3. The pre-spinning pressurized inclined sealing lip structure according to claim 1, characterized in that: The cross-sectional shape of the gradually expanding twisted groove (6) is rectangular.

4. The pre-spinning pressurized inclined sealing lip structure according to claim 1, characterized in that: The number of the gradually expanding twisted grooves (6) is an integer multiple of the number of turbine blades (11).

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