High-precision rectification assembly of gas turbine

Abstract

The high-precision rectification assembly comprises a rectification plate, the rectification plate comprises an outer rectification plate body and an inner rectification plate body, a through hole is formed in the outer rectification plate body, the inner rectification plate body is arranged in the through hole, an annular flow guide groove is formed in the inner ring face of the through hole, and a plurality of fan blades are installed on the outer ring face of the inner rectification plate body in an annular structure. The fan blades all extend into the annular flow guide groove, an air inlet channel for blowing the fan blades and the rectification inner plate to rotate is arranged on one side of the annular flow guide groove, and an air outlet channel for exhausting air is arranged on the side, located on the air inlet channel, of the annular flow guide groove. According to the utility model, the structure is simple, one part of air flow can enter the annular flow guide groove along the air inlet hopper and the air inlet channel, and the rectification inner plate is driven to rotate by pushing the fan blades, so that the other part of air discharged from the flow guide holes can be rotatably discharged, and the uniformity of air flow distribution is improved, so as to ensure the combustion effect.

Description

TECHNICAL FIELD

[0001] The utility model relates to gas turbine technical field, concretely relates to a high accuracy rectifier assembly of gas turbine. BACKGROUND

[0002] Gas turbine: gas turbine is with continuous flow gas as working medium drive impeller high speed rotation, the energy of fuel is changed into useful work internal combustion power machine, is a kind of rotary vane type heat engine. The rectifier of gas turbine in prior art has the following problems:

[0003] At present, the rectifier of gas turbine in prior art, due to its structure is relatively simple, can only make the airflow in gas turbine pass through rectifier, cannot make the airflow passing through contact with fuel in nozzle evenly, thereby affecting the combustion effect of fuel in nozzle. SUMMARY

[0004] The utility model provides a high accuracy rectifier assembly of gas turbine, and the airflow is discharged by the rotation of rectifier inner plate, to solve the problem in the background art.

[0005] The utility model is realized through the following technical scheme: a kind of high accuracy rectifier assembly of gas turbine, including rectifier plate, the rectifier plate includes rectifier outer plate and rectifier inner plate, the rectifier outer plate is equipped with through-hole, rectifier inner plate is set in through-hole, and ring-shaped flow guide groove is equipped on the inner circle surface of through-hole, and the outer circle surface of rectifier inner plate is installed with multiple fan blades in ring-shaped structure, and fan blade extends into ring-shaped flow guide groove, and the side of ring-shaped flow guide groove is equipped with the air inlet channel of blowing fan blade and rectifier inner plate rotation, and the side of ring-shaped flow guide groove located in air inlet channel is equipped with the air outlet channel of discharging gas.

[0006] As preferred technical scheme, air inlet channel is horizontally oriented towards fan blade, and the end of air inlet channel away from ring-shaped flow guide groove is curved to form air inlet hole towards one side of rectifier outer plate, and air inlet hole is installed with air inlet hopper outside, and the end of air outlet channel away from ring-shaped flow guide groove is curved to form air outlet hole towards the other side of rectifier outer plate, and air inlet hole and air outlet hole are arranged in front and back.

[0007] As preferred technical scheme, rectifier inner plate is distributed with flow guide hole, and flow guide hole is evenly distributed in ring-shaped structure.

[0008] As preferred technical scheme, the width of fan blade is matched with the width of ring-shaped flow guide groove, the height of fan blade is matched with the height of ring-shaped flow guide groove, and the outer side of fan blade is arranged in arc structure.

[0009] As preferred technical scheme, the outer side of rectifier outer plate and rectifier inner plate is flush.

[0010] Preferably, the opening on the outer side of the air inlet hopper has an inner diameter larger than that of the air inlet hole.

[0011] The utility model discloses the beneficial effect is: the utility model discloses simple structure, a part of airflow can enter annular flow groove along air inlet hopper and air inlet channel, the rotation of rectifying inner plate is driven through the mode of pushing fan blade, make another part of the gas that discharges from flow hole can rotate and discharge, increase the uniformity of airflow distribution, to ensure the combustion effect. BRIEF DESCRIPTION OF DRAWINGS

[0012] In order to more clearly illustrate the technical scheme in the embodiments of the utility model or prior art, below will to the embodiment or prior art description needed to use the drawing briefly introduce, obviously, the drawing in the following description only some embodiments of the utility model, for those skilled in the art, under the premise of not paying creative labor, still can obtain other drawings according to these drawings.

[0013] Figure 1 It is the overall structure schematic diagram of the utility model;

[0014] Figure 2 It is the side view of the utility model;

[0015] Figure 3 It is the structure schematic diagram of rectifying outer plate of the utility model;

[0016] Figure 4 It is the sectional view of the utility model.

[0017] Wherein, 1, rectifying outer plate;2, rectifying inner plate;3, flow hole;4, air inlet hole;5, air inlet hopper;6, air outlet hole;7, through hole;8, annular flow groove;9, fan blade;10, air inlet channel;11, air outlet channel. DETAILED DESCRIPTION

[0018] The embodiments of the utility model will be described in detail below, the example of the embodiment is shown in the drawings, wherein the same or similar reference numerals represent the same or similar elements or elements with the same or similar function throughout. The embodiments described below by referring to the drawings are exemplary, only for explaining the utility model, and can not be understood as limiting the utility model.

[0019] All features disclosed in this specification, or the steps in all disclosed methods or processes, can be combined in any manner, except for mutually exclusive features and / or steps.

[0020] Any feature in the foregoing specification (including any accompanying claims, abstract and drawings) can be replaced by alternative features serving the same, equivalent or similar purpose, unless expressly stated otherwise. That is, unless expressly stated otherwise, every feature disclosed is one example only of a generic series of equivalent or similar features.

[0021] As Figure 1 , Figure 2 , Figure 3 and Figure 4 indicated, the utility model discloses a high -precision fairing subassembly of gas turbine, including fairing board, the fairing board includes fairing outer board 1 and fairing inner board 2, be equipped with through -hole 7 on the fairing outer board 1, and the fairing inner board 2 is arranged in through -hole 7, and the inner circle face on through -hole 7 is equipped with annular flow guide groove 8, and the outer circle face on the fairing inner board 2 is installed with multiple fan blade 9 in annular structure, and the fan blade 9 all extends into annular flow guide groove 8, and one side of annular flow guide groove 8 is equipped with the air inlet channel 10 of blowing fan blade 9 and fairing inner board 2 rotation, and one side of annular flow guide groove 8 located in air inlet channel 10 is equipped with the air outlet channel 11 of discharging gas.

[0022] In the embodiment, the air inlet channel 10 is horizontally arranged towards the fan blade 9, the end of the air inlet channel 10 away from the annular flow guide groove 8 is bent towards one side of the fairing outer board 1 to form an air inlet hole 4, the air inlet hole 4 is externally mounted with an air inlet funnel 5, the end of the air outlet channel 11 away from the annular flow guide groove 8 is bent towards the other side of the fairing outer board 1 to form an air outlet hole 6, and the air inlet hole 4 and the air outlet hole 6 are arranged in front of and behind each other.

[0023] In the embodiment, the fairing inner board 2 is covered with flow guide holes 3, and the flow guide holes 3 are arranged in an annular structure and uniformly distributed.

[0024] In the embodiment, the width of the fan blade 9 matches the width of the annular flow guide groove 8, the height of the fan blade 9 matches the height of the annular flow guide groove 8, and the outer side of the fan blade 9 is arranged in an arc structure, so that the annular flow guide groove is divided into multiple chambers by the multiple fan blades, so that the blown airflow can enter each chamber and drive the rotation of each fan blade.

[0025] In the embodiment, the outer sides of the fairing outer board 1 and the fairing inner board 2 are arranged in a flush manner.

[0026] In the embodiment, the opening outer diameter of the air inlet funnel 5 is larger than the inner diameter of the air inlet hole 4, so that the airflow outside can be collected by the large-diameter air inlet funnel and quickly enter the air inlet channel.

[0027] Part of the air flow can enter into the annular flow guide groove along the air inlet funnel and the air inlet channel, the entered air can push the fan blade to rotate along the annular flow guide groove, the rotation of the fan blade drives the rectification inner plate, wherein the discharged air flow can finally be discharged along the air outlet channel and the air outlet hole, so that the air flow forms a convection effect, to ensure the efficiency of rotation, so that another part of the air discharged from the flow guide hole can be driven by the rotating rectification inner plate, so that this part of the air flow can be discharged while rotating, increase the uniformity of air flow distribution, and increase the combustion quality.

[0028] The above merely describes a specific implementation of the present application, but the protection scope of the present application is not limited to this. Any change or replacement without creative labor should be covered in the protection scope of the present application. Therefore, the protection scope of the present application should be limited by the protection scope defined in the claims.

Claims

1. A high-precision fairing assembly for a gas turbine engine, characterized by: The utility model relates to a rectifier plate, which comprises a rectifier outer plate (1) and a rectifier inner plate (2), wherein the rectifier outer plate (1) is provided with a through hole (7), the rectifier inner plate (2) is arranged in the through hole (7), an annular flow guide groove (8) is arranged on the inner ring surface of the through hole (7), a plurality of fan blades (9) are arranged on the outer ring surface of the rectifier inner plate (2) in an annular structure, the fan blades (9) all extend into the annular flow guide groove (8), one side of the annular flow guide groove (8) is provided with an air inlet channel (10) for driving the fan blades (9) and the rectifier inner plate (2) to rotate, and one side of the annular flow guide groove (8) located at the air inlet channel (10) is provided with an air outlet channel (11) for discharging gas.

2. The high-precision rectifying assembly of a gas turbine according to claim 1, characterized in that: The air inlet channel (10) is horizontally arranged towards the fan blades (9), one end of the air inlet channel (10) away from the annular flow guide groove (8) is bent towards one side of the rectifier outer plate (1) to form an air inlet hole (4), an air inlet funnel (5) is arranged outside the air inlet hole (4), one end of the air outlet channel (11) away from the annular flow guide groove (8) is bent towards the other side of the rectifier outer plate (1) to form an air outlet hole (6), and the air inlet hole (4) and the air outlet hole (6) are arranged in front of and behind each other.

3. The high-precision rectifying assembly of a gas turbine according to claim 1, characterized in that: The rectifier inner plate (2) is provided with flow guide holes (3) arranged in an annular structure.

4. The high precision flow straightening assembly of a gas turbine according to claim 1, characterized in that: The width of the fan blades (9) is matched with the width of the annular flow guide groove (8), the height of the fan blades (9) is matched with the height of the annular flow guide groove (8), and the outer side of the fan blades (9) is arranged in an arc structure.

5. The high precision flow straightening assembly of a gas turbine according to claim 1, characterized in that: The outer sides of the rectifier outer plate (1) and the rectifier inner plate (2) are arranged in a flush manner.

6. The high precision flow straightening assembly of a gas turbine according to claim 2, characterized in that: The opening outer diameter of the air inlet funnel (5) is greater than the inner diameter of the air inlet hole (4).

Images