阅读说明：本技术 一种尾气透平、静叶及动叶 (Tail gas turbine, stationary blade and movable blade ) 是由 汪传美 陈红梅 陈党民 张利民 郑秀萍 杨星 张小龙 高少华 杨岐平 邱启家 杨 于 2019-09-16 设计创作，主要内容包括：本发明提供了一种尾气透平、静叶及动叶,包括机匣和安装在机匣内的转轴,机匣上安装有静叶,转轴的轮毂上安装有动叶,机匣上沿着轴向依次安装有5级静叶,转轴上沿着轴向依次安装有5级动叶,静叶和动叶依次交替布设。所述的5级静叶分别为一级静叶、二级静叶、三级静叶、四级静叶和五级静叶；所述的5级动叶分别为一级动叶、二级动叶、三级动叶、四级动叶和五级动叶；本发明的尾气透平与已知的四级尾气透平相比,效率大幅提升,最终优化方案的效率提升了2.23％,以17400kw的尾气透平为例,节能效果在原有方案基础上,每年可多回收约300万度电。(The invention provides a tail gas turbine, static blades and movable blades, which comprises a casing and a rotating shaft arranged in the casing, wherein the casing is provided with the static blades, the hub of the rotating shaft is provided with the movable blades, the casing is sequentially provided with 5 stages of static blades along the axial direction, the rotating shaft is sequentially provided with 5 stages of movable blades along the axial direction, and the static blades and the movable blades are sequentially and alternately arranged. The 5-stage static blades are respectively a first-stage static blade, a second-stage static blade, a third-stage static blade, a fourth-stage static blade and a fifth-stage static blade; the 5 stages of movable blades are respectively a first stage movable blade, a second stage movable blade, a third stage movable blade, a fourth stage movable blade and a fifth stage movable blade; compared with the known four-stage tail gas turbine, the tail gas turbine has the advantages that the efficiency is greatly improved, the efficiency of the final optimization scheme is improved by 2.23%, and about 300 ten thousand DEG of electricity can be recycled each year on the basis of the original scheme by taking the 17400kw tail gas turbine as an example.)

1. A tail gas turbine comprises a casing (1) and a rotating shaft (2) installed in the casing (1), wherein a static blade (4) is installed on the casing (1), and a movable blade (5) is installed on a hub (3) of the rotating shaft (2), and is characterized in that 5 stages of static blades (4) are sequentially installed on the casing (1) along the axial direction, 5 stages of movable blades (5) are sequentially installed on the rotating shaft (2) along the axial direction, and the static blades (4) and the movable blades (5) are sequentially and alternately arranged;

the 5-stage static blades (4) are respectively a first-stage static blade (401), a second-stage static blade (402), a third-stage static blade (403), a fourth-stage static blade (404) and a fifth-stage static blade (405); the blade profile parameters at the blade profile diameter equalizing position of the 5-stage stationary blade (4) are respectively as follows:

the first-stage stationary blade (401) is 53.0mm in chord length, 35.1mm in blade width, 19.1mm in maximum thickness, 3.5 degrees in inlet geometric angle, 77.8 degrees in outlet geometric angle, 39.8mm in pitch and 10.3mm in throat width;

the second-stage stationary blade (402) has the chord length of 43.6mm, the blade width of 29mm, the maximum thickness of 15.4mm, the inlet geometric angle of-10.5 degrees, the outlet geometric angle of 76.7 degrees, the pitch of 34.6mm and the throat width of 10.1 mm;

the three-stage stationary blade (403) has the chord length of 43.6mm, the blade width of 29.7mm, the maximum thickness of 15.4mm, the inlet geometric angle of-10.9 degrees, the outlet geometric angle of 75.4 degrees, the pitch of 34.6mm and the throat width of 10.6 mm;

the four-stage stationary blade (404) has the chord length of 45.4mm, the blade width of 30.7mm, the maximum thickness of 16.3mm, the inlet geometric angle of-13.4 degrees, the outlet geometric angle of 76.1 degrees, the pitch of 33.4mm and the throat width of 10.5 mm;

the five-stage stationary blade (405) has the chord length of 49.6mm, the blade width of 36.8mm, the maximum thickness of 17.2mm, the inlet geometric angle of-15.3 degrees, the outlet geometric angle of 71.6 degrees, the pitch of 36.0mm and the throat width of 12.8 mm;

the 5-stage movable blade (5) is respectively a first-stage movable blade (501), a second-stage movable blade (502), a third-stage movable blade (503), a fourth-stage movable blade (504) and a fifth-stage movable blade (505), and the blade profile parameters at the blade profile uniform diameter of the 5-stage movable blade (5) are respectively as follows:

the chord length of the first-stage movable blade (501) is 45.5mm, the blade width is 30.2mm, the maximum thickness is 16.4mm, the inlet geometric angle is-11.9 degrees, the outlet geometric angle is 77.7 degrees, the pitch is 36.0mm, and the throat width is 9.4 mm;

the chord length of the secondary movable blade (502) is 45.7mm, the blade width is 31.4mm, the maximum thickness is 16.7mm, the inlet geometric angle is-9.7 degrees, the outlet geometric angle is 74.8 degrees, the pitch is 32.8mm, and the throat width is 9.2 mm;

the chord length of the three-stage movable blade (503) is 51.4mm, the blade width is 35mm, the maximum thickness is 16.7mm, the inlet geometric angle is-4.8 degrees, the outlet geometric angle is 74.6 degrees, the pitch is 30.5mm, and the throat width is 7.9 mm;

the four-stage movable blade (504) has the chord length of 59mm, the blade width of 41.2mm, the maximum thickness of 19.2mm, the inlet geometric angle of-1.2 degrees, the outlet geometric angle of 72.7 degrees, the pitch of 34mm and the throat width of 9.4 mm;

the five-stage movable blade (505) has the chord length of 65.5mm, the blade width of 51.4mm, the maximum thickness of 11.5mm, the inlet geometric angle of-11.9 degrees, the outlet geometric angle of 67.2 degrees, the pitch of 37mm and the throat width of 12.5 mm.

2. The exhaust turbine according to claim 1, wherein the number of the first stage turbine vanes (401) is 56, the number of the second stage turbine vanes (402) is 60, the number of the third stage turbine vanes (403) is 60, the number of the fourth stage turbine vanes (404) is 62, and the number of the fifth stage turbine vanes (405) is 62.

3. The exhaust gas turbine according to claim 1, wherein the number of the first-stage movable blades (501) is 62, the number of the second-stage movable blades (502) is 68, the number of the third-stage movable blades (503) is 68, the number of the fourth-stage movable blades (504) is 61, and the number of the fifth-stage movable blades (505) is 56.

4. A stator blade, characterized in that the profile at the profile mean diameter of the stator blade is characterized by: the chord length is 43.6mm, the blade width is 29mm, the maximum thickness is 15.4mm, the inlet geometric angle is-10.5 degrees, the outlet geometric angle is 76.7 degrees, the pitch is 34.6mm, and the throat width is 10.1 mm.

5. A stator blade, characterized in that the profile at the profile mean diameter of the stator blade is characterized by: the chord length is 43.6mm, the blade width is 29.7mm, the maximum thickness is 15.4mm, the inlet geometric angle is-10.9 degrees, the outlet geometric angle is 75.4 degrees, the pitch is 34.6mm, and the throat width is 10.6 mm.

6. A stator blade, characterized in that the profile at the profile mean diameter of the stator blade is characterized by: the chord length is 45.4mm, the blade width is 30.7mm, the maximum thickness is 16.3mm, the inlet geometric angle is-13.4 degrees, the outlet geometric angle is 76.1 degrees, the pitch is 33.4mm, and the throat width is 10.5 mm.

7. A movable vane is characterized in that the vane profile at the vane profile uniform diameter of the movable vane is as follows: the chord length is 51.4mm, the blade width is 35mm, the maximum thickness is 16.7mm, the inlet geometric angle is-4.8 degrees, the outlet geometric angle is 74.6 degrees, the pitch is 30.5mm, and the throat width is 7.9 mm.

8. A movable vane is characterized in that the vane profile at the vane profile uniform diameter of the movable vane is as follows: the chord length is 59mm, the blade width is 41.2mm, the maximum thickness is 19.2mm, the inlet geometric angle is-1.2 degrees, the outlet geometric angle is 72.7 degrees, the pitch is 34mm, and the throat width is 9.4 mm.

9. A movable vane is characterized in that the vane profile at the vane profile uniform diameter of the movable vane is as follows: the chord length is 65.5mm, the blade width is 51.4mm, the maximum thickness is 11.5mm, the inlet geometric angle is-11.9 degrees, the outlet geometric angle is 67.2 degrees, the pitch is 37mm, and the throat width is 12.5 mm.

Technical Field

The invention belongs to the field of nitric acid, relates to a nitric acid four-in-one unit adopting a double-pressurization method, and particularly relates to a tail gas turbine, a stationary blade and a movable blade.

Background

Nitric acid is a basic product in chemical industry, and has important application in chemical fertilizer, organic, fuel, paint, printing and dyeing, plastics, metallurgy, national defense and other industries, and the consumption of nitric acid is the largest in chemical industry.

Along with the adjustment of economic and industrial structures, in the face of increasingly strict requirements on safety and environmental protection, the double-pressurization method nitric acid production with obvious energy-saving and emission-reduction effects is favored, and the technical development of a high-efficiency, energy-saving and environmental-friendly four-in-one unit is also driven.

In order to get rid of the situation that the nitric acid four-in-one unit is limited by people in China, the localization of the nitric acid four-in-one unit is from inexistence to existence, and the product development is upgraded and upgraded, and the improvement is continuously improved.

The tail of the nitric acid four-in-one unit is used as an energy-saving device, and the performance of the nitric acid four-in-one unit directly determines the energy-saving level of the whole nitric acid four-in-one unit.

A tail gas energy recovery turbine device, called a tail gas turbine or tail gas turbine for short, and a domestic tail gas technology form a mature and reliable turbine development system through investigation, summary of design experience and multiple technical promotion of field operation for nearly 20 years, and a reaction type three-dimensional crankle blade is developed on the basis, so that the tail gas turbine or tail gas turbine has high tail gas turbine efficiency and good variable working condition performance.

In order to further improve the energy-saving effect of the tail penetration, the performance of the tail penetration improving technology needs to be further improved, and particularly, the current market tends to be large-scale, so that the energy-saving benefit brought by the tail penetration improving technology is more obvious.

Disclosure of Invention

Aiming at the defects in the prior art, the invention aims to provide a fixed blade and a movable blade of a tail gas turbine, solve the technical problem that the energy-saving effect of the tail gas turbine in the prior art needs to be further improved, and further improve the energy-saving effect of tail gas turbine in a breakthrough manner.

In order to solve the technical problems, the invention adopts the following technical scheme:

the utility model provides a tail gas turbine, includes the casing and installs the pivot in the casing, installs quiet leaf on the casing, installs the movable blade on the wheel hub of pivot, installs 5 grades of quiet leaves along the axial on the casing in proper order, installs 5 grades of movable blades along the axial in proper order in the pivot, and quiet leaf and movable blade are laid in turn in proper order.

The 5-stage static blades are respectively a first-stage static blade, a second-stage static blade, a third-stage static blade, a fourth-stage static blade and a fifth-stage static blade; the blade profile parameters at the blade profile uniform diameter position of the 5-stage stationary blade are respectively as follows:

the first-stage stationary blade is 53.0mm in chord length, 35.1mm in blade width, 19.1mm in maximum thickness, 3.5 degrees in inlet geometric angle, 77.8 degrees in outlet geometric angle, 39.8mm in pitch and 10.3mm in throat width;

the second-stage stationary blade is 43.6mm in chord length, 29mm in blade width, 15.4mm in maximum thickness, minus 10.5 degrees in inlet geometric angle, 76.7 degrees in outlet geometric angle, 34.6mm in pitch and 10.1mm in throat width;

the third-stage stationary blade has the chord length of 43.6mm, the blade width of 29.7mm, the maximum thickness of 15.4mm, the inlet geometric angle of-10.9 degrees, the outlet geometric angle of 75.4 degrees, the pitch of 34.6mm and the throat width of 10.6 mm;

the four-stage stationary blade has the chord length of 45.4mm, the blade width of 30.7mm, the maximum thickness of 16.3mm, the inlet geometric angle of-13.4 degrees, the outlet geometric angle of 76.1 degrees, the pitch of 33.4mm and the throat width of 10.5 mm;

the five-stage stationary blade has the chord length of 49.6mm, the blade width of 36.8mm, the maximum thickness of 17.2mm, the inlet geometric angle of-15.3 degrees, the outlet geometric angle of 71.6 degrees, the pitch of 36.0mm and the throat width of 12.8 mm;

the 5-stage movable blades are respectively a first-stage movable blade, a second-stage movable blade, a third-stage movable blade, a fourth-stage movable blade and a fifth-stage movable blade, and the blade profile parameters at the blade profile uniform diameter positions of the 5-stage movable blades are respectively as follows:

the first-stage movable blade has the chord length of 45.5mm, the blade width of 30.2mm, the maximum thickness of 16.4mm, the inlet geometric angle of-11.9 degrees, the outlet geometric angle of 77.7 degrees, the pitch of 36.0mm and the throat width of 9.4 mm;

the chord length of the secondary movable blade is 45.7mm, the blade width is 31.4mm, the maximum thickness is 16.7mm, the inlet geometric angle is-9.7 degrees, the outlet geometric angle is 74.8 degrees, the pitch is 32.8mm, and the throat width is 9.2 mm;

the chord length of the three-stage movable blade is 51.4mm, the blade width is 35mm, the maximum thickness is 16.7mm, the inlet geometric angle is-4.8 degrees, the outlet geometric angle is 74.6 degrees, the pitch is 30.5mm, and the throat width is 7.9 mm;

the four-stage movable blade has the chord length of 59mm, the blade width of 41.2mm, the maximum thickness of 19.2mm, the inlet geometric angle of-1.2 degrees, the outlet geometric angle of 72.7 degrees, the pitch of 34mm and the throat width of 9.4 mm;

the five-stage movable blade has the chord length of 65.5mm, the blade width of 51.4mm, the maximum thickness of 11.5mm, the inlet geometric angle of-11.9 degrees, the outlet geometric angle of 67.2 degrees, the pitch of 37mm and the throat width of 12.5 mm.

The invention also has the following technical characteristics:

the number of the first-stage stator vanes is 56, the number of the second-stage stator vanes is 60, the number of the third-stage stator vanes is 60, the number of the fourth-stage stator vanes is 62, and the number of the fifth-stage stator vanes is 62.

The number of the first-stage movable blades is 62, the number of the second-stage movable blades is 68, the number of the third-stage movable blades is 68, the number of the fourth-stage movable blades is 61, and the number of the fifth-stage movable blades is 56.

The invention also protects a stator blade, and the blade profile at the blade profile uniform diameter part of the stator blade is characterized in that: the chord length is 43.6mm, the blade width is 29mm, the maximum thickness is 15.4mm, the inlet geometric angle is-10.5 degrees, the outlet geometric angle is 76.7 degrees, the pitch is 34.6mm, and the throat width is 10.1 mm.

The invention also protects a stator blade, and the blade profile at the blade profile uniform diameter part of the stator blade is characterized in that: the chord length is 43.6mm, the blade width is 29.7mm, the maximum thickness is 15.4mm, the inlet geometric angle is-10.9 degrees, the outlet geometric angle is 75.4 degrees, the pitch is 34.6mm, and the throat width is 10.6 mm.

The invention also protects a stator blade, and the blade profile at the blade profile uniform diameter part of the stator blade is characterized in that: the chord length is 45.4mm, the blade width is 30.7mm, the maximum thickness is 16.3mm, the inlet geometric angle is-13.4 degrees, the outlet geometric angle is 76.1 degrees, the pitch is 33.4mm, and the throat width is 10.5 mm.

The invention also protects a movable blade, and the blade profile at the blade profile uniform diameter part of the movable blade is characterized in that: the chord length is 51.4mm, the blade width is 35mm, the maximum thickness is 16.7mm, the inlet geometric angle is-4.8 degrees, the outlet geometric angle is 74.6 degrees, the pitch is 30.5mm, and the throat width is 7.9 mm.

The invention also protects a movable blade, and the blade profile at the blade profile uniform diameter part of the movable blade is characterized in that: the chord length is 59mm, the blade width is 41.2mm, the maximum thickness is 19.2mm, the inlet geometric angle is-1.2 degrees, the outlet geometric angle is 72.7 degrees, the pitch is 34mm, and the throat width is 9.4 mm.

The invention also protects a movable blade, and the blade profile at the blade profile uniform diameter part of the movable blade is characterized in that: the chord length is 65.5mm, the blade width is 51.4mm, the maximum thickness is 11.5mm, the inlet geometric angle is-11.9 degrees, the outlet geometric angle is 67.2 degrees, the pitch is 37mm, and the throat width is 12.5 mm.

Compared with the prior art, the invention has the following technical effects:

compared with the known four-stage tail gas turbine, the tail gas turbine has the advantages that the efficiency is greatly improved, the efficiency of the final optimization scheme is improved by 2.23%, and about 300 ten thousand DEG of electricity can be recycled each year on the basis of the original scheme by taking the 17400kw tail gas turbine as an example.

Drawings

FIG. 1 is a schematic view of the structure of stationary blades, movable blades, meridian flow channels and flow channel mean diameter.

FIG. 2 is a schematic structural diagram of geometric parameters of the airfoil at the mean diameter of the airfoil.

Fig. 3(a) and (b) are total pressure schematics of CFD calculated for the 4-stage version of comparative example 1 and the 5-stage version of comparative example 2.

Fig. 3(c) and (d) are schematic diagrams of the moving blade relative velocity vectors of the 4-stage scheme of comparative example 1 and the 5-stage scheme of comparative example 2 calculated by CFD.

Fig. 4 is a schematic structural view of the upper and lower wall surfaces of a radial flow passage of an exhaust gas turbine according to the present invention.

FIG. 5 is a two-dimensional configuration schematic of the second, third and fourth stage vanes of the present invention.

FIG. 6 is a three-dimensional structural schematic of the second, third and fourth stage vanes of the present invention.

FIG. 7 is a two-dimensional structural schematic of the three, four and five stage buckets of the present invention.

FIG. 8 is a three-dimensional structural schematic of the three, four and five stage buckets of the present invention.

FIG. 9 is a two-dimensional comparison schematic representation of the profiles of the second, third, and fourth stage vanes of the present invention with the second, third, and fourth stage vanes of comparative example 2.

FIG. 10 is a two-dimensional comparison schematic representation of the blade profiles of a three-stage, four-stage, and five-stage bucket of the present invention and a three-stage, four-stage, and five-stage bucket of comparative example 2.

The meaning of the individual reference symbols in the figures is: 1-a casing, 2-a rotating shaft, 3-a hub, 4-a stationary blade, 5-a movable blade and 6-a flow channel with uniform diameter; 401-first stage stator blade, 402-second stage stator blade, 403-third stage stator blade, 404-fourth stage stator blade, 405-fifth stage stator blade; 501-a first-stage bucket, 502-a second-stage bucket, 503-a third-stage bucket, 504-a fourth-stage bucket, 505-a fifth-stage bucket.

The present invention will be explained in further detail with reference to examples.

Detailed Description

In the present invention, the upper wall surface and the lower wall surface of the radial flow channel are shown in fig. 1, the upper wall surface of the radial flow channel is the casing 1, and the lower wall surface of the radial flow channel is the hub 3. The profile parameters at the profile mean diameter are shown in FIG. 2. In the figure, the chord length is L₁Leaf width of D₁The maximum thickness is d, the inlet geometric angle is alpha, the outlet geometric angle is beta, and the pitch is L₂Throat width of D₂。

In the present invention, CFD refers to computational fluid dynamic analysis. The efficiency of the tail gas turbine is isentropic and is calculated or obtained by adopting a CFD method. The CFD method is a common method known in the art.

The following embodiments of the present invention are provided, and it should be noted that the present invention is not limited to the following embodiments, and all equivalent changes based on the technical solutions of the present invention are within the protection scope of the present invention.