High-pressure turbine blade tip sealing device structure with active clearance control function

Abstract

The invention discloses an active clearance control high-pressure turbine blade tip sealing device structure, which is characterized in that after being introduced into an inner cavity from an air inlet in a turbine case, cooling air enters a heat insulation cavity formed by a left heat insulation sleeve, a right heat insulation sleeve and a throttling ring through an air hole A in the left heat insulation sleeve, and enters a sealing block assembly after being throttled through an air hole B in the throttling ring; the pressure and flow of airflow in an inner cavity of the sealing ring assembly are adjusted, it is guaranteed that the sealing block assembly actively controls gaps between the sealing block assembly and a baffle ring and between the sealing block assembly and a turbine case, the sealing block assembly is cooled, under different working states of an engine, the sealing ring assembly always keeps a reasonable sealing gap between the sealing ring assembly and a blade tip of a high-pressure turbine blade, gas leakage is reduced, and the service life of the engine is prolonged. The problem that in the prior art, a gap between a sealing ring assembly and a blade tip cannot be actively adjusted to guarantee the sealing effect under different working conditions is solved.

Description

Technical Field

[0001] The present invention relates to a tip sealing device structure for a high-pressure turbine blade with active clearance control, belonging to the technical field of aero-engines. Background Art

[0002] As a key core component of an aero-engine, the working efficiency of a turbine blade is a main index affecting the engine performance. High-temperature and high-pressure gas flows through the turbine component, converting thermal energy and pressure potential energy into gas kinetic energy and mechanical work. The gas pressure and temperature change violently along the axial direction. Due to the clearance between the rotating part and the stator part of the turbine, gas leakage in the main flow path of the turbine is inevitable. Gas leakage will affect the working efficiency of the turbine blade and cause engine performance loss. Therefore, it is necessary to design a sealing structure to reduce gas leakage in the main flow path of the turbine and improve engine performance.

[0003] The existing tip sealing structure for a high-pressure turbine blade (see Chinese Patent Publication No. CN107435563B) is a fixed sealing structure with a coating added at the tip contact. It cannot actively adjust the clearance between the sealing ring assembly and the tip to ensure the sealing effect under different working conditions. Summary of the Invention

[0004] To solve the above technical problems, the present invention provides a tip sealing device structure for a high-pressure turbine blade with active clearance control.

[0005] The present invention is achieved through the following technical solutions.

[0006] A tip sealing device structure for a high-pressure turbine blade with active clearance control provided by the present invention includes:

[0007] A tip sealing device structure for a high-pressure turbine blade that can achieve active clearance control.

[0008] It includes a sealing ring assembly, a turbine casing, and a throttle ring.

[0009] An air inlet hole for cooling gas to enter is provided on the leading edge of the turbine casing; the air inlet holes are several in number and are evenly spaced on the turbine casing.

[0010] The inner cavity of the turbine casing is fixedly assembled with a left heat insulation sleeve, a right heat insulation sleeve, and a throttle ring; several air holes A are provided on the left heat insulation sleeve, and several air holes B are provided on the throttle ring.

[0011] The air holes A are aligned with the air inlet holes; the sealing ring assembly is installed at the bottom of the radial inner surface of the turbine casing.

[0012] The sealing ring assembly is assembled with the throttle ring through a pin B, and the sealing ring assembly and the throttle ring are limited by the pin B to prevent axial movement.

[0013] The turbine casing is provided with inclined holes for the extension of pin B; the bottom of the seal ring assembly is coated with a coating.

[0014] A retaining ring is installed on the front side of the turbine casing through pin A, and the retaining ring holds the front side of the seal ring assembly; the retaining ring is fixed to the turbine casing through a plate; there is a gap between the seal ring assembly and the retaining ring and the radial space of the turbine casing after assembly, and the throttle ring is located at the radial back of the seal ring assembly.

[0015] The turbine casing is provided with inclined holes for the extension of pin A.

[0016] The beneficial effects of the present invention are as follows: After the cooling air is introduced from the air inlet hole on the turbine casing into the inner cavity, it enters the heat insulation cavity formed by the left heat insulation sleeve, the right heat insulation sleeve, and the throttle ring through the air hole A on the left heat insulation sleeve, and after being throttled by the air hole B on the throttle ring, it enters the seal block assembly, adjusting the pressure and flow rate of the air flow in the inner cavity of the seal ring assembly, ensuring that the seal block assembly actively controls the gap between the retaining ring and the turbine casing, and cooling the seal block assembly. Under different working conditions of the engine, the seal ring assembly always maintains a reasonable sealing gap with the tip of the high-pressure turbine blade, reducing gas leakage, and solving the problem that the prior art cannot actively adjust the gap between the seal ring assembly and the tip to ensure the sealing effect under different working conditions. BRIEF DESCRIPTION OF THE DRAWINGS

[0017] Figure 1 It is a schematic cross-sectional view of the structure from the axonometric perspective of the present invention;

[0018] Figure 2 It is a schematic distribution diagram of the cross-sectional view of the present invention;

[0019] Figure 3 It is a schematic cross-sectional view of the present invention with pin A and pin B distributed;

[0020] Figure 4 It is a schematic structure diagram of the right heat insulation sleeve of the present invention;

[0021] Figure 5 It is a top view schematic diagram of the throttle ring of the present invention;

[0022] Figure 6 It is a schematic distribution diagram of the seal ring assembly, the throttle ring, pin A, and pin B of the present invention;

[0023] In the figure: 1 - left heat insulation sleeve; 2 - plate; 3 - retaining ring; 4 - seal ring assembly; 5 - turbine casing; 6 - air inlet hole; 7 - right heat insulation sleeve; 8 - throttle ring; 9 - pin A; 10 - pin B; 11 - air hole A; 12 - air hole B. DETAILED DESCRIPTION OF THE INVENTION

[0024] The technical solution of the present invention will be further described below, but the scope of protection claimed is not limited thereto.

[0025] As Figures 1 to 6 shown.

[0026] The structure of a tip sealing device for a high-pressure turbine blade with active clearance control in the present application includes:

[0027] A turbine casing 5 provided with air inlet holes 6 on the leading edge, where the air inlet holes 6 are several in number and evenly spaced on the turbine casing 5 for cooling gas to enter.

[0028] A left heat insulation sleeve 1, a right heat insulation sleeve 7 and a throttle ring 8 are spot-welded and fixedly assembled in the inner cavity of the turbine casing 5; a number of air holes A11 are provided on the left heat insulation sleeve 1, and a number of air holes B12 are provided on the throttle ring; the air holes A11 are aligned with the air inlet holes 6, and the cooling gas enters from the air inlet holes 6 and then flows to the air holes B12 through the air holes A11.

[0029] A sealing ring assembly 4 is installed at the bottom of the radial inner surface of the turbine casing 5. The sealing ring assembly 4 is assembled with the throttle ring 8 through a pin B10. The sealing ring assembly 4 and the throttle ring 8 are limited by the pin B10 to prevent axial movement (i.e., Figure 1 left-right movement), so that the sealing ring assembly 4 and the throttle ring 8 can only slide radially based on the pin B10 (i.e., Figure 1 up-down movement). The pin A9 and the pin B10 both extend into the inclined holes provided in the turbine casing 5.

[0030] A coating for sealing is applied to the bottom of the sealing ring assembly 4 to form a tip of the high-pressure turbine blade in combination with the high-pressure turbine blade.

[0031] A retaining ring 3 is installed on the front side of the turbine casing 5 through a pin A9. The retaining ring 3 holds the front side of the sealing ring assembly 4; the retaining ring 3 is fixedly welded to the turbine casing 5 through a plate 2. There is a gap in the radial space between the sealing ring assembly 4, the retaining ring 3 and the turbine casing 5 after assembly, and the throttle ring 8 is located at the radial back of the sealing ring assembly 4. The cooling gas is transferred from the air holes B12 of the throttle ring 8 to the radial back of the sealing ring assembly 4 for cooling.

[0032] After the cooling air introduced through the air inlet hole 6 on the turbine casing 5 enters the inner cavity, it enters the heat insulation cavity formed by the left heat insulation sleeve 1, the right heat insulation sleeve 7, and the throttle ring 8 through the air hole A11 on the left heat insulation sleeve 1, and enters the seal block assembly 4 after throttling through the air hole B12 on the throttle ring 8, adjusting the pressure and flow rate of the air flow in the inner cavity of the seal ring assembly 4, ensuring that the seal block assembly 4 actively controls the clearance between the retaining ring 3 and the turbine casing 5, and cooling the seal block assembly 4. Under different operating conditions of the engine, the seal ring assembly 4 always maintains a reasonable sealing clearance with the tip of the high-pressure turbine blade, reducing gas leakage, and solving the problem that the prior art cannot actively adjust the clearance between the seal ring assembly and the blade tip to ensure the sealing effect under different working conditions.

Claims

1. A high-pressure turbine blade tip sealing device structure with active clearance control, characterized in that: include: A high-pressure turbine blade tip sealing device structure capable of realizing active clearance control.

2. The active clearance controlled high pressure turbine blade tip sealing device structure according to claim 1, characterized in that: It comprises a sealing ring assembly (4), a turbine casing (5), and a throttle ring (8).

3. The active clearance controlled high pressure turbine blade tip sealing device structure as claimed in claim 2, characterized in that: An air inlet (6) for cooling gas to enter is arranged on the front edge of the turbine casing (5); the air inlet holes (6) are in a plurality and are evenly spaced and distributed on the turbine casing (5).

4. The active clearance controlled high pressure turbine blade tip sealing device structure as claimed in claim 3, characterized in that: The inner cavity of the turbine casing (5) is fixedly equipped with a left heat insulation sleeve (1), a right heat insulation sleeve (7) and a throttle ring (8); the left heat insulation sleeve (1) is provided with a plurality of air holes A (11), and the throttle ring is provided with a plurality of air holes B (12).

5. The active clearance controlled high pressure turbine blade tip sealing device structure as claimed in claim 4, characterized in that: The air hole A (11) is aligned with the air inlet hole (6); and a sealing ring assembly (4) is installed at the bottom of the radial inner surface of the turbine casing (5).

6. The active clearance controlled high pressure turbine blade tip sealing device structure as claimed in claim 4, characterized in that: The sealing ring assembly (4) is assembled with the throttle ring (8) via a pin B (10), and the sealing ring assembly (4) and the throttle ring (8) are limited by the pin B (10) to prohibit axial movement.

7. The active clearance controlled high pressure turbine blade tip sealing device structure as claimed in claim 4, characterized in that: The turbine casing (5) is provided with an oblique hole for the pin B (10) to extend; the bottom of the sealing ring assembly (4) is coated.

8. The active clearance controlled high pressure turbine blade tip sealing device structure as claimed in claim 2, characterized in that: A retaining ring (3) is installed on the front side of the turbine casing (5) through a pin A (9), and the retaining ring (3) drags the front side of the sealing ring assembly (4); the retaining ring (3) is fixed to the turbine casing (5) through a plate (2); after the sealing ring assembly (4) is assembled, there is a gap between the retaining ring (3) and the turbine casing (5) in the radial space, and the throttle ring (8) is located at the radial back of the sealing ring assembly (4).

9. The active clearance controlled high pressure turbine blade tip sealing device structure as claimed in claim 8, characterized in that: The turbine casing (5) is provided with an oblique hole for the pin A (9) to extend.

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