Flue gas turbine for improving energy recovery efficiency of flue gas turbine

Abstract

The utility model discloses a flue gas turbine for improving the energy recovery efficiency of the flue gas turbine, which comprises an outer ring shell, a rotating disc of the flue gas turbine is connected in the outer ring shell through a rotating shaft, a plurality of moving blades are connected around the outer periphery of the rotating disc, the moving blades are twisted composite blade type blades, and each moving blade comprises a mounting seat positioned at the bottom, the mounting seat is connected with a blade part, the blade part comprises a triangular plate and an arc-shaped plate connected with the triangular plate, the triangular plate and the arc-shaped plate are twisted clockwise, and the flue gas turbine stator blade has the technical characteristics that the pressure loss can be reduced, the flue gas pressure at the flue gas turbine stator blade is improved, the power recovery is improved, and the like.

Description

Technical Field

[0001] The utility model relates to a gas turbine, and more specifically to a gas turbine for improving the energy recovery efficiency of a gas turbine, belonging to the field of gas turbines. Background Art

[0002] At present, for a heavy oil catalytic cracking unit with an annual output of 4.5 million tons, its main blower set consists of a gas turbine + an axial flow compressor + a motor / generator. Among them, the gas turbine and the electric / generator jointly drive the axial flow compressor to supply air to the regeneration system of the unit. The gas turbine utilizes the heat energy and pressure energy contained in the flue gas from coking regeneration to expand and do work, recovering the energy of the high-temperature flue gas, and the insufficient power part is provided by the electric / generator. Since the gas turbine has a single-stage cantilever structure with axial inlet and vertical upward exhaust, the actual operating conditions deviate from the design conditions, the inlet pressure of the gas turbine fails to reach the design requirements, and the energy recovery efficiency of the gas turbine is low. Summary of the Utility Model

[0003] In order to solve the above-mentioned problems in the prior art, the utility model provides a gas turbine for improving the energy recovery efficiency of a gas turbine, which has the technical features of being able to reduce pressure loss, increase the flue gas pressure at the stator blades of the gas turbine, and improve power recovery.

[0004] In order to achieve the above object, the utility model is realized by the following technical solutions:

[0005] A gas turbine for improving the energy recovery efficiency of a gas turbine according to the utility model includes an outer ring housing. Inside the outer ring housing, a rotating disk of the gas turbine is connected through a rotating shaft. A plurality of moving blades are connected around the outer periphery of the rotating disk. The moving blades are twisted composite profile blades, which include a mounting seat at the bottom. A blade part is connected to the mounting seat. The blade part includes a triangular piece and an arc piece connected to the triangular piece. Both the triangular piece and the arc piece are twisted in the clockwise direction.

[0006] Preferably, the outer edge of the arc piece is designed to be arc-shaped and the middle of the outer edge is higher than both sides.

[0007] Preferably, from the bottom of the mounting seat upwards, the edge at the connection of the triangular piece and the arc piece bends outwards and is inclined.

[0008] Preferably, both sides of the mounting seat are beveled edges, and a plurality of arc-shaped protrusions are protruded on the beveled edges at intervals. An arc-shaped groove is formed on the rotating disk. The mounting seat is slidably embedded in the arc-shaped groove on the rotating disk through the arc-shaped protrusions to realize the connection of the moving blade to the rotating disk.

[0009] Preferably, the diameter of the outer ring housing is 1790 mm.

[0010] Preferably, the arc-shaped protrusion is a falcon tooth.

[0011] Beneficial effects: It can reduce the flow area, reduce the pressure loss, increase the flue gas pressure at the static blades of the gas turbine, recover more potential energy, improve the power recovery, and achieve the improvement of the energy recovery efficiency of the gas turbine; the structure is simple and the practicability is strong. BRIEF DESCRIPTION OF THE DRAWINGS

[0012] Figure 1 is a schematic diagram of the overall structure of the present invention.

[0013] Figure 2 is one of the schematic diagrams of the moving blade structure of the present invention.

[0014] Figure 3 is another schematic diagram of the moving blade structure of the present invention.

[0015] Figure 4 is yet another schematic diagram of the moving blade structure of the present invention.

[0016] Figure 5 is still another schematic diagram of the moving blade structure of the present invention.

[0017] Figure 6 is one more schematic diagram of the moving blade structure of the present invention.

[0018] Figure 7 is yet one more schematic diagram of the moving blade structure of the present invention.

[0019] Figure 8 is still yet another schematic diagram of the moving blade structure of the present invention. DETAILED DESCRIPTION OF THE INVENTION

[0020] The present invention will be further described below with reference to the accompanying drawings of the specification, but the present invention is not limited to the following embodiments.

[0021] As Figure 1-8 shown is a specific embodiment of a gas turbine for improving the energy recovery efficiency of a gas turbine. This embodiment is a gas turbine for improving the energy recovery efficiency of a gas turbine, including an outer ring housing 1. Inside the outer ring housing 1, a rotating disc 2 of the gas turbine is connected by a rotating shaft. A plurality of moving blades 3 are connected around the outer periphery of the rotating disc 2. The moving blades 3 are twisted composite profile blades, which include a mounting seat 4 at the bottom. The mounting seat 4 is connected with a blade part, as Figure 2 , 4 , 5 shown. The blade part includes a triangular piece 5 and an arc-shaped piece 6 connected to the triangular piece 5, as Figure 7-8As shown, the triangular piece 5 and the arcuate piece 6 are twisted in a clockwise direction. The structural design of the present application can effectively adjust the distribution shape of the isobars, inhibit the separation of the boundary layer at the root, reduce secondary flow losses, and make the flow in the low-energy zone flow toward the mainstream, thereby improving the aerodynamic efficiency of the moving blade 3, increasing the working capacity of the moving blade 3, and improving the recovery efficiency of the flue gas turbine. Furthermore, in order to increase the strength of the blade root and avoid fatigue fracture of the blade root after long-term high-temperature operation of the moving blade 3, the length of the moving blade 3 is reduced by 50mm, and the diameter of the traditional flue gas turbine inlet flow passage is reduced from 1890mm to 1790mm. The reduced diameter further ensures the throttling effect of the flue gas turbine. The mounting base 4, triangular piece 5, and arcuate piece 6 are preferably integrally formed.

[0022] Existing technology: Before the transformation, the pressure behind the butterfly valve at the flue gas turbine inlet is 0.15Mpa.

[0023] The design scheme proposed in this application aims to reduce the pressure behind the flue gas turbine inlet butterfly valve to 0.20 MPa. This improvement significantly increases the turbine's energy recovery efficiency by approximately 0.05 MPa. This increase in intake pressure can significantly improve the turbine's energy recovery efficiency, saving 42.8 MW·h of electricity annually. Furthermore, by reducing the length of the flue gas turbine's moving blades, the centrifugal force on the blade tenons is reduced, increasing the allowable strength safety margin of the blade root tenons. This reduces the contact stress level at the root of the moving blade tenons by approximately 15%, significantly improving the reliability of the moving blades and extending their service life while maintaining their original safe operation.

[0024] In a preferred embodiment, the outer edge of the arc-shaped piece 6 is designed to be arc-shaped and the middle of the outer edge is higher than the two sides. Figure 3 As shown, the edges of the connection between the triangular piece 5 and the arc-shaped piece 6 are bent outward and tilted, so that the flow in the low-energy area flows toward the mainstream, thereby improving the aerodynamic efficiency of the moving blade 3.

[0025] In a preferred embodiment, the mounting base 4 has beveled sides with multiple spaced arcuate protrusions 7 protruding from these beveled sides. The rotating disc 2 is provided with an arcuate groove, through which the mounting base 4 slides and fits into the arcuate groove on the rotating disc 2, thereby connecting the moving blade 3 to the rotating disc 2. The arcuate protrusions 7 are falcon teeth. This facilitates installation and improves blade positioning accuracy, ensures the designed installation angle, and enhances energy recovery efficiency.

[0026] Finally, it should be noted that the present invention is not limited to the above embodiments and may be subject to many variations. All variations that can be directly derived or associated with the content disclosed by a person skilled in the art should be considered to be within the scope of protection of the present invention.

Claims

1. A gas turbine for improving the energy recovery efficiency of a gas turbine, characterized in that: It includes an outer ring housing (1), inside which a rotating disc (2) of a gas turbine is connected by a rotating shaft. A number of moving blades (3) are connected around the outer periphery of the rotating disc (2). The moving blades (3) are twisted composite profile blades, which include a mounting seat (4) at the bottom. A blade part is connected to the mounting seat (4). The blade part includes a triangular piece (5) and an arc piece (6) connected to the triangular piece (5). The triangular piece (5) and the arc piece (6) are both twisted in the clockwise direction.

2. The gas turbine for improving the energy recovery efficiency of the gas turbine according to claim 1, wherein: The outer edge of the arc piece (6) is designed in an arc shape and the middle of the outer edge is higher than both sides.

3. The gas turbine for improving the energy recovery efficiency of the gas turbine according to claim 2, wherein: From the bottom of the mounting seat (4) upwards, the edge at the connection of the triangular piece (5) and the arc piece (6) bends outwards and is inclined.

4. A gas turbine for improving the energy recovery efficiency of a gas turbine according to claim 1, characterized in that: Both sides of the mounting seat (4) are in the shape of beveled edges, and a plurality of arc-shaped protrusions (7) arranged at intervals protrude from the beveled edges. An arc-shaped groove is formed on the rotating disc (2). The mounting seat (4) is slidably inserted into the arc-shaped groove on the rotating disc (2) through the arc-shaped protrusions (7) to connect the moving blade (3) to the rotating disc (2).

5. A gas turbine for improving the energy recovery efficiency of a gas turbine according to claim 1, characterized in that: The diameter of the outer ring housing (1) is 1790 mm.

6. A gas turbine for improving the energy recovery efficiency of a gas turbine according to claim 4, characterized in that: The arc-shaped protrusion (7) is a falcon tooth.

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