Honeycomb sealing system of prewhirl device for gas turbine
By setting up a pre-rotation device in front of the honeycomb sealing system of the gas turbine, increasing the air flow rate, changing the inflow direction, reducing the temperature, and blocking the air blending of high and low temperature chambers, the problems of slow air flow rate, high temperature and air blending in the prior art are solved, and the lower temperature cooling air supply and component cooling are achieved.
Patent Information
- Application Number
- CN202510271695.5
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2025-03-09
- Publication Date
- 2025-06-06
AI Technical Summary
In the honeycomb seal structure of the secondary air system of the existing gas turbine, the air flow rate is slow and the inlet temperature is high, resulting in an increase in the outlet temperature and the high-temperature chamber and the low-temperature chamber are mixed with the air in the low-temperature chamber.
A pre-rotating device honeycomb sealing system is designed. By setting a pre-rotating device before the honeycomb sealing, the air flow rate is increased, the air flow direction is changed, the air temperature is reduced, and the air blending of the high-temperature chamber and the low-temperature chamber are blocked through the channel structure.
It effectively reduces the air outlet temperature after the honeycomb sealing system, provides a lower temperature cooling air, which is conducive to the cooling of parts and reduces the cooling air temperature by 50±10℃.
Smart Images
Figure CN120100541A_ABST
Abstract
Description
Technical Field
[0001] The present invention relates to a sealing system, in particular to a sealing system of a gas turbine. Background Art
[0002] At present, the honeycomb seal of the secondary air system of the gas turbine generally adopts a comb-tooth honeycomb seal structure, that is, the turbine rotor is processed into a comb-tooth structure composed of several gas seal teeth, and the corresponding turbine stator is installed with a honeycomb seal, thereby forming a honeycomb seal system between the rotor and the stator. The air flows into the high-pressure chamber in front of the honeycomb seal system, and flows into the low-pressure chamber behind it after passing through the honeycomb seal system. This process is an entropy increase process. Since the air flow speed in the chamber before the honeycomb seal is slow, and the rotor rotation produces a high temperature rise, the cooling air has a high temperature before entering the honeycomb seal, and the air temperature will further increase after the cooling air passes through the honeycomb seal. Summary of the invention
[0003] The object of the present invention is to provide a honeycomb sealing system with a pre-swirl device for a gas turbine, which can increase the flow rate of air before it enters the honeycomb seal, change the direction of air entering the honeycomb seal, reduce the temperature of air entering the honeycomb sealing system, and at the same time block the mixing of high-temperature chamber and low-temperature chamber air.
[0004] The object of the present invention is achieved in that:
[0005] The present invention discloses a honeycomb sealing system for a pre-swirl device of a gas turbine, which is characterized in that it comprises a stator, a rotor, and a pre-swirl device, a comb-tooth-shaped gas sealing structure composed of comb teeth is processed on the top of the rotor, a honeycomb seal is installed at a position of the stator corresponding to the comb teeth, a pre-swirl device is arranged in front of the honeycomb seal, the pre-swirl device is fixed on the stator, a pre-swirl device inlet and a pre-swirl device outlet are respectively arranged on the pre-swirl device, and a gap is left between the end of the pre-swirl device and the rotor.
[0006] The present invention may also include:
[0007] 1. The inlet of the pre-swirling device is connected to the high-pressure chamber, and the outlet of the pre-swirling device is a series of grooves. The sum of the cross-sectional areas of all the grooves is smaller than the cross-sectional area of the inlet of the pre-swirling device.
[0008] 2. The angle between the groove and the engine axis is 75°, and the groove outlet has a matching velocity triangle with the honeycomb seal and comb-tooth air seal structure.
[0009] 3. A second cavity is formed inside the pre-swirl device, a third cavity is formed by the pre-swirl device and the rotor in front of the honeycomb seal, a fourth cavity is formed in front of the pre-swirl device, and a fifth cavity is formed by the stator and the rotor behind the honeycomb seal. The cooling air enters the second cavity from the high-pressure cavity and enters the third cavity through the outlet of the pre-selection device. After that, a part of the cooling air flows radially inward into the fourth cavity, and the other part of the cooling air flows into the fifth cavity through the honeycomb seal and the comb-shaped air seal structure.
[0010] 4. The comb teeth of the comb-tooth-shaped air sealing structure include 7 rows.
[0011] 5. The series of grooves is 45 grooves of φ1.6.
[0012] The advantages of the present invention are: the pre-spin device honeycomb sealing system of the present invention effectively reduces the outlet temperature of the honeycomb sealing system, provides cooling air with a lower temperature, and is conducive to the cooling of the parts after the honeycomb sealing system. Compared with the honeycomb sealing system without a pre-spin device, the cooling air temperature is reduced by 50±10℃, which provides more protection for the cooling of the parts after the pre-spin device honeycomb sealing system. BRIEF DESCRIPTION OF THE DRAWINGS
[0013] Figure 1 It is a structural schematic diagram of the present invention;
[0014] Figure 2 It is a working principle diagram of the present invention;
[0015] Figure 3 Schematic diagram of the slot angle. DETAILED DESCRIPTION
[0016] The present invention is described in more detail below with reference to the accompanying drawings:
[0017] Combination Figure 1-3 The appearance characteristics of the present invention are shown in the figure. The entire pre-swirl device honeycomb sealing system consists of a pre-swirl device 1 and a honeycomb sealing system. The honeycomb sealing system consists of a rotor 3 and a stator 2. The top of the rotor is processed into a comb-tooth-shaped air seal structure composed of 7 comb teeth 5. The stator is installed with a honeycomb seal 4 at the position corresponding to the rotor comb teeth. The pre-swirl device inlet 6 is connected to the high-pressure air chamber and has a large flow area. The pre-swirl device outlet 7 is composed of 45 φ1.6 grooves, and the total area of the grooves is much smaller than the pre-swirl device inlet area. The angle between the pre-swirl device groove and the engine axis is 75°, and the groove outlet and the honeycomb sealing system have a matching speed triangle. The groove is used to increase the flow rate of air through the pre-swirl device, change the outlet direction of air through the pre-swirl device, and reduce the temperature of air through the pre-swirl device. There is a designed small gap 8 between the inner diameter of the pre-swirl device and the rotor to block the cooling air of the high-temperature chamber from flowing to the low-temperature chamber.
[0018] Figure 2This is an implementation method of the working principle of the honeycomb sealing system of the pre-swirl device of the present invention. First, cooling air flows from the high-pressure chamber 1 into the pre-swirl device, enters the internal chamber 2 of the pre-swirl device, and flows through the outlet of the pre-swirl device. The cooling air with higher temperature and pressure inside the pre-swirl device expands at the outlet of the pre-swirl device, the cooling air speed increases, the temperature decreases, and forms a designed angle with the engine axis to match the engine rotor speed so that the cooling air has the designed working parameters when entering the honeycomb seal. After the cooling air flows out from the outlet of the pre-swirl device and enters the chamber 3, a part of the cooling air flows radially inward into the chamber 4 to prevent the high-temperature air in the chamber 4 from mixing with the air in the chamber 3; the other part of the cooling air enters the honeycomb sealing system at a lower temperature according to the designed working parameters, and finally flows into the chamber 5 at the rear of the honeycomb sealing system.
[0019] Figure 3 It is a cross-sectional schematic diagram of the pre-swirl device of the present invention, showing the structural dimensional parameters of the outlet channel of the pre-swirl device in this embodiment. The angle between the pre-swirl device and the engine axis is 75 degrees, and the outlet of the pre-swirl device is composed of 45 φ1.6 circular holes.
Claims
1. A honeycomb sealing system for a pre-swirl device of a gas turbine, characterized in that: The invention comprises a stator, a rotor and a pre-swirl device. A comb-tooth-shaped air seal structure composed of comb teeth is processed on the top of the rotor. A honeycomb seal is installed at the position of the stator corresponding to the comb teeth. A pre-swirl device is arranged in front of the honeycomb seal. The pre-swirl device is fixed on the stator. A pre-swirl device inlet and a pre-swirl device outlet are respectively arranged on the pre-swirl device. A gap is left between the end of the pre-swirl device and the rotor.
2. The honeycomb sealing system for a pre-swirl device of a gas turbine according to claim 1, characterized in that: The inlet of the pre-swirling device is connected to the high-pressure chamber, and the outlet of the pre-swirling device is a series of grooves, and the sum of the cross-sectional areas of all the grooves is smaller than the cross-sectional area of the inlet of the pre-swirling device.
3. The honeycomb sealing system for a pre-swirl device for a gas turbine according to claim 2, characterized in that: The angle between the groove and the engine axis is 75°, and the groove outlet has a matching velocity triangle with the honeycomb seal and comb-tooth air seal structure.
4. The honeycomb sealing system for a pre-swirl device for a gas turbine according to claim 1, characterized in that: A second cavity is formed inside the pre-swirl device, a third cavity is formed by the pre-swirl device and the rotor in front of the honeycomb seal, a fourth cavity is formed in front of the pre-swirl device, and a fifth cavity is formed by the stator and the rotor behind the honeycomb seal. The cooling air enters the second cavity from the high-pressure cavity and enters the third cavity through the outlet of the pre-selection device. After that, a part of the cooling air flows radially inward into the fourth cavity, and the other part of the cooling air flows into the fifth cavity through the honeycomb seal and the comb-shaped air seal structure.
5. The honeycomb sealing system for a pre-swirl device for a gas turbine according to claim 1, characterized in that: The comb teeth of the comb-tooth-shaped air sealing structure include 7 rows.
6. The honeycomb sealing system for a pre-swirl device for a gas turbine according to claim 2, characterized in that: The series of grooves consists of 45 grooves with a diameter of φ1.6.