CN112682112A - Two-stage gas turbine, stationary blade and movable blade for two-stage gas turbine - Google Patents
Two-stage gas turbine, stationary blade and movable blade for two-stage gas turbine Download PDFInfo
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Abstract
本发明提供了一种两级煤气透平、用于两级煤气透平的静叶及动叶，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两级静叶，转轴上沿着轴向依次安装有两级动叶，静叶和动叶依次交替布设。两级静叶分别为一级静叶、二级静叶；所述的两级动叶分别为一级动叶、二级动叶；本发明的煤气透平与已知的两级煤气透平相比，效率大幅提升，最终优化方案的效率提升了3％，以20000kw的煤气透平为例，节能效果在原有方案基础上，每年可多回收约480万度电/台。
The invention provides a two-stage gas turbine, a stationary blade and a moving blade for the two-stage gas turbine, comprising a casing and a rotating shaft installed in the casing. A moving blade is installed, two-stage stationary blades are installed on the casing in sequence along the axial direction, and two-stage moving blades are sequentially installed along the axial direction on the rotating shaft, and the stationary blades and the moving blades are arranged alternately in turn. The two-stage stator blades are respectively a first-stage stator blade and a second-stage stator blade; the two-stage moving blades are respectively a first-stage moving blade and a second-stage moving blade; the gas turbine of the present invention is different from the known two-stage gas turbine. In comparison, the efficiency has been greatly improved, and the efficiency of the final optimization scheme has increased by 3%. Taking a 20,000kw gas turbine as an example, the energy saving effect is based on the original scheme, and about 4.8 million kWh/unit can be recovered every year.
Description
Technical Field
The invention belongs to the field of blast furnace metallurgy, relates to an energy recovery turbine unit, and particularly relates to a two-stage gas turbine, and a stationary blade and a movable blade for the two-stage gas turbine.
Background
A blast furnace gas residual pressure turbine power generation device is high-efficiency energy-saving equipment for recovering blast furnace gas energy and adjusting furnace top pressure in a blast furnace iron-making process, and belongs to a technologically intensive turbine machine.
At present, the development trend of blast furnaces is towards medium and large scale development, and higher requirements are put on the high efficiency of blast furnace gas energy recovery turbines. The efficiency of the blast furnace gas energy recovery turbine blade profile is directly determined, so that the blast furnace process needs to be matched, a new blade profile is developed, and the efficiency of the energy recovery turbine is further improved.
Disclosure of Invention
Aiming at the defects in the prior art, the invention aims to provide a two-stage gas turbine, a static blade and a movable blade for the two-stage gas turbine, solve the technical problem that the energy-saving effect of the gas turbine in the prior art needs to be further improved, and further improve the energy-saving effect of the gas turbine in a breakthrough manner.
In order to solve the technical problems, the invention adopts the following technical scheme:
a two-stage gas turbine comprises a casing and a rotating shaft arranged in the casing, wherein the casing is provided with static blades, a hub of the rotating shaft is provided with movable blades, the casing is sequentially provided with two stages of static blades along the axial direction, the rotating shaft is sequentially provided with two stages of movable blades along the axial direction, and the static blades and the movable blades are sequentially and alternately arranged;
the two stages of static blades are respectively a first stage static blade and a second stage static blade;
the two stages of movable blades are respectively a first stage movable blade and a second stage movable blade;
the first-stage static blade, the second-stage static blade, the first-stage movable blade and the second-stage movable blade respectively comprise three blade profile sections which are respectively a first blade profile section, a second blade profile section and a third blade profile section, and each of the first blade profile section, the second blade profile section and the third blade profile section comprises a pressure surface blade profile line and a suction surface blade profile line;
the first blade profile section of the first-stage stator blade has the section height of 532mm, and the pressure surface blade profile line of the first blade profile section is-4 multiplied by 10-5x3-0.004x2-0.677x-9.123, suction profile of first profile cross-section y-1 x 10-5x3-0.012x2-0.765x+22.63；
The section height of the second blade section of the first-stage stator blade is 654mm, and the pressure surface blade profile line of the second blade section is-3 multiplied by 10-5x3-0.003x2-0.659x-10.99, and the profile line of the suction profile of the second blade section is-8 x 10-6x3-0.010x2-0.731x+27.75；
The third blade section of the first-stage stator blade has a section height of 837mm and a pressure of the third blade sectionThe force surface blade profile line is y ═ 2x 10-5x3-0.002x2-0.659x-15.21, suction profile of third profile cross-section is-8 × 10 ═ y-6x3-0.008x2-0.682x+35.98；
The section height of the first blade profile section of the second-stage stator blade is 534mm, and the pressure surface blade profile line of the first blade profile section is-9 multiplied by 10-5x3-0.009x2-0.712x-6.257, suction profile of first profile cross-section y-9 × 10-5x3-0.018x2-0.691x+21.04；
The second blade section of the second-stage stationary blade has a section height of 676mm, and the pressure surface profile line of the second blade section is-5 × 10 ═ y-5x3-0.007x2-0.631x-6.790, suction profile of the second vane section having a vane profile y-6 × 10-5x3-0.013x2-0.596x+26.7；
The height of the section of the third blade-shaped section of the second-stage stationary blade is 889 mm; the pressure profile line of the third blade profile section is y-3 × 10-5x3-0.004x2-0.772x-14.95, and the suction profile of the third profile section is-5 × 10-5x3-0.011x2-0.684x+36.02；
The first blade profile section of the first-stage movable blade has the section height of 560mm, and the pressure surface blade profile line of the first blade profile section is-4 multiplied by 10-6x3-0.002x2-0.150x-14.96, suction profile of first profile cross-section is y ═ 8x 10-6x3-0.004x2-0.102x+47.74；
The section height of the second blade section of the first-stage movable blade is 664mm, and the pressure surface blade profile line of the second blade section is-4 multiplied by 10-6x3-0.003x2-0.638x-10.33, suction profile of second vane cross-section is-1 × 10-5x3-0.007x2-0.592x+41.57；
The third blade profile section of the first-stage movable blade has a section height of 872mm, and the pressure surface profile line of the third blade profile section is 3 multiplied by 10-5x3-0.004x2-1.837x-5.573, and the profile of the suction profile of the third profile cross-section is y 5 × 10-5x3-0.009x2-1.899x+26.10；
The section height of the first blade profile section of the secondary movable blade is 560mm, and the pressure surface blade profile line of the first blade profile section is-5 multiplied by 10-6x3-0.002x2-0.118x-18.42, suction profile of first profile cross-section is-1 × 10-5x3-0.004x2-0.070x+49.15；
The second blade section of the second-stage movable blade has a section height of 740mm, and the pressure surface profile line of the second blade section is y equal to 6 multiplied by 10-6x3-0.004x2-1.100x-12.87, suction profile of second blade section is y ═ 5x 10-6x3-0.010x2-1.042x+39.20；
The third blade profile section of the secondary movable blade has a section height of 920mm, and the pressure surface profile line of the third blade profile section is y 3 multiplied by 10-5x3-0.003x2-1.994x-8.547, suction profile of third profile cross-section y 3 × 10-5x3-0.009x-1.993x+24.47；
Wherein:
x and y are respectively an abscissa and an ordinate in an Oxyz coordinate system; z is a vertical coordinate in an Oxyz coordinate system;
in an Oxyz coordinate system, the rotation center of a gas turbine where the blade is located is taken as a horizontal coordinate x, and the height direction of the blade passing through the gravity center of the blade is taken as a vertical coordinate z, namely the direction of the height of the cross sections of the first blade-shaped cross section, the second blade-shaped cross section and the third blade-shaped cross section; the intersection point of the horizontal coordinate x and the vertical coordinate z is used as a coordinate origin O, namely a projection point of the gravity center of the blade on the horizontal coordinate x along the vertical coordinate z is used as the coordinate origin O; the direction passing through the origin O of coordinates and perpendicular to the Oxz plane is taken as the ordinate y.
The invention also has the following technical characteristics:
the number of the first-stage stator vanes is 28, and the number of the second-stage stator vanes is 34.
The number of the first-stage movable blades is 23, and the number of the second-stage movable blades is 23.
The invention also protects a stator blade for a two-stage gas turbine, which comprises three blade-shaped sections, namely a first blade-shaped section, a second blade-shaped section and a third blade-shaped section, wherein each of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section comprises a pressure surface blade-shaped profile and a suction surface blade-shaped profile;
the first blade profile section of the stator blade has a section height of 532mm, and the pressure surface profile line of the first blade profile section is-4 x 10 ═ y-5x3-0.004x2-0.677x-9.123, suction profile of first profile cross-section y-1 x 10-5x3-0.012x2-0.765x+22.63；
The second blade section of the stator blade has a section height of 654mm, and the pressure surface profile of the second blade section is-3 × 10-5x3-0.003x2-0.659x-10.99, and the profile line of the suction profile of the second blade section is-8 x 10-6x3-0.010x2-0.731x+27.75；
The third blade section of the stator blade has a section height of 837mm, and the pressure surface blade profile line of the third blade section is-2 x 10 ═ y-5x3-0.002x2-0.659x-15.21, suction profile of third profile cross-section is-8 × 10 ═ y-6x3-0.008x2-0.682x+35.98。
The invention also protects a stator blade for a two-stage gas turbine, which comprises three blade-shaped sections, namely a first blade-shaped section, a second blade-shaped section and a third blade-shaped section, wherein each of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section comprises a pressure surface blade-shaped profile and a suction surface blade-shaped profile;
the first blade profile section of the stator blade has a section height of 534mm, and the pressure surface profile line of the first blade profile section is-9 x 10 ═ y-5x3-0.009x2-0.712x-6.257, suction profile of first profile cross-section y-9 × 10-5x3-0.018x2-0.691x+21.04；
The second blade section of the stator blade has a section height of 676mm, and the pressure surface profile line of the second blade section is-5 × 10 ═-5x3-0.007x2-0.631x-6.790, suction profile of the second vane section having a vane profile y-6 × 10-5x3-0.013x2-0.596x+26.7；
The height of the section of the third blade-shaped section of the static blade is 889 mm; the pressure profile line of the third blade profile section is y-3 × 10-5x3-0.004x2-0.772x-14.95, and the suction profile of the third profile section is-5 × 10-5x3-0.011x2-0.684x+36.02。
The invention also protects a movable vane for a two-stage gas turbine, which comprises three blade sections, namely a first blade section, a second blade section and a third blade section, wherein each of the first blade section, the second blade section and the third blade section comprises a pressure surface blade profile line and a suction surface blade profile line;
the section height of the first blade section of the movable blade is 560mm, and the pressure surface blade profile line of the first blade section is-4 multiplied by 10-6x3-0.002x2-0.150x-14.96, suction profile of first profile cross-section is y ═ 8x 10-6x3-0.004x2-0.102x+47.74；
The section height of the second blade section of the movable blade is 664mm, and the pressure surface blade profile line of the second blade section is that y is-4 multiplied by 10-6x3-0.003x2-0.638x-10.33, suction profile of second vane cross-section is-1 × 10-5x3-0.007x2-0.592x+41.57；
The third blade section of the movable blade has a section height of 872mm, and the pressure surface profile line of the third blade section is 3 × 10-5x3-0.004x2-1.837x-5.573, and the profile of the suction profile of the third profile cross-section is y 5 × 10- 5x3-0.009x2-1.899x+26.10。
The invention also protects a movable blade for a two-stage gas turbine, which is characterized by comprising three blade profile sections, namely a first blade profile section, a second blade profile section and a third blade profile section, wherein each of the first blade profile section, the second blade profile section and the third blade profile section comprises a pressure surface blade profile line and a suction surface blade profile line;
the section height of the first blade section of the movable blade is 560mm, and the pressure surface blade profile line of the first blade section is-5 multiplied by 10-6x3-0.002x2-0.118x-18.42, suction profile of first profile cross-section is-1 × 10-5x3-0.004x2-0.070x+49.15；
The height of the second blade section of the movable blade is 740mm, and the pressure surface profile line of the second blade section is y equal to 6 multiplied by 10-6x3-0.004x2-1.100x-12.87, suction profile of second blade section is y ═ 5x 10- 6x3-0.010x2-1.042x+39.20；
The third blade section of the movable blade has a section height of 920mm, and the pressure surface blade profile line of the third blade section is 3x 10-5x3-0.003x2-1.994x-8.547, suction profile of third profile cross-section y 3 × 10- 5x3-0.009x-1.993x+24.47。
Compared with the prior art, the invention has the following technical effects:
compared with the existing two-stage gas turbine, the gas turbine has the advantages that the efficiency is greatly improved, the efficiency is improved by 3 percent to the maximum extent, and by taking 20000kw gas turbine as an example, the energy-saving effect is that about 480 ten thousand DEG of electricity can be recycled each year on the basis of the existing two-stage gas turbine.
Drawings
FIG. 1 is a schematic view of a vane, a blade, and a meridian flow passage.
FIG. 2 is a schematic view of three profile cross-sectional positions of each moving and stationary blade and corresponding profile lines of the pressure surface and the suction surface.
Fig. 3(a) is a schematic diagram of the total pressure distribution of example 1 calculated by CFD.
Fig. 3(b) is a velocity vector distribution diagram of embodiment 1 of CFD calculation.
FIG. 4 is a schematic view showing the structure of the upper and lower wall surfaces of a radial flow channel of a gas turbine according to the present invention.
FIG. 5 is a two-dimensional structural schematic of a two-stage moving vane of the present invention.
FIG. 6 is a three-dimensional configuration of a first and second stage moving vane of the present invention.
FIG. 7 is a two-dimensional structure schematic diagram of a secondary moving vane of comparative example 1.
Fig. 8 is a three-dimensional structural schematic view of a secondary moving vane of comparative example 1.
The meaning of the individual reference symbols in the figures is: 1-a casing, 2-a rotating shaft, 3-a hub, 4-a static blade and 5-a movable blade; 401-first stage stationary blade, 402-second stage stationary blade; 501-first stage moving blade, 502-second stage moving blade.
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 three blade profile section positions of each moving and static blade and the corresponding pressure surface and suction surface blade profile lines are shown in fig. 2, and each pressure surface or suction surface blade profile line is fitted to obtain a corresponding blade profile line function.
In FIG. 2, A-A is a first profile section, B-B is a second profile section, C-C is a third profile section, A-A-a is a pressure profile line of the first profile section, A-A-B is a suction profile line of the first profile section; B-B-a is a pressure surface blade profile line of the second blade profile section, B-B-B is a suction surface blade profile line of the second blade profile section, C-C-a is a pressure surface blade profile line of the third blade profile section, and C-C-B is a suction surface blade profile line of the third blade profile section; hAIs the height of the first profile section, HBHeight of the second blade profile section, HCThe height of the third profile section.
In the invention, the first blade profile section is the section of the blade profile closest to the rotation center; the third blade profile section is the section with the blade profile furthest from the rotation center; the second airfoil section is one airfoil section between the first airfoil section and the third airfoil section.
In the invention:
x and y are respectively an abscissa and an ordinate in an Oxyz coordinate system; z is a vertical coordinate in an Oxyz coordinate system;
in an Oxyz coordinate system, the rotation center of a gas turbine where the blade is located is taken as a horizontal coordinate x, and the height direction of the blade passing through the gravity center of the blade is taken as a vertical coordinate z, namely the direction of the height of the cross sections of the first blade-shaped cross section, the second blade-shaped cross section and the third blade-shaped cross section; the intersection point of the horizontal coordinate x and the vertical coordinate z is used as a coordinate origin O, namely a projection point of the gravity center of the blade on the horizontal coordinate x along the vertical coordinate z is used as the coordinate origin O; the direction passing through the origin O of coordinates and perpendicular to the Oxz plane is taken as the ordinate y.
In the Oxyz coordinate system, x, y and z are all in mm.
The blade is a vane or a blade.
In the invention, the first blade-shaped section, the second blade-shaped section and the third blade-shaped section are all sections parallel to the Oxy plane, namely are all sections vertical to the vertical coordinate z. The height of the first blade-shaped section, the height of the second blade-shaped section and the height of the third blade-shaped section are the height from the xy plane of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section, respectively, i.e., the distance from the rotation center of the gas turbine to the first blade-shaped section, the second blade-shaped section and the third blade-shaped section.
In the invention, the first blade-shaped section, the second blade-shaped section and the third blade-shaped section are all sections parallel to the Oxy plane, namely are all sections vertical to the vertical coordinate z. The height of the first blade-shaped section, the height of the second blade-shaped section and the height of the third blade-shaped section are the height from the xy plane of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section, respectively, i.e., the distance from the rotation center of the gas turbine to the first blade-shaped section, the second blade-shaped section and the third blade-shaped section.
In the present invention, CFD refers to computational fluid dynamic analysis. The efficiency of the gas turbine is isentropic and is calculated or obtained by adopting a CFD (computational fluid dynamics) 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.
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.
Example 1:
following the above technical solution, as shown in fig. 3 to fig. 6, the present embodiment provides a two-stage gas turbine, which includes a casing 1 and a rotating shaft 2 installed in the casing 1, wherein a stationary blade 4 is installed on the casing 1, a movable blade 5 is installed on a hub 3 of the rotating shaft 2, two stages of stationary blades 4 are sequentially installed on the casing 1 along an axial direction, two stages of movable blades 5 are sequentially installed on the rotating shaft 2 along the axial direction, and the stationary blades 4 and the movable blades 5 are sequentially and alternately arranged;
the two stages of the stator blades 4 are a first stage stator blade 401 and a second stage stator blade 402 respectively;
the two-stage movable blades 5 are a first-stage movable blade 501 and a second-stage movable blade 502 respectively;
the first-stage stationary blade 401, the second-stage stationary blade 402, the first-stage movable blade 501 and the second-stage movable blade 502 respectively comprise three blade-shaped sections which are respectively a first blade-shaped section, a second blade-shaped section and a third blade-shaped section, and each of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section comprises a pressure surface blade-shaped line and a suction surface blade-shaped line;
specifically, the first vane cross section of the first-stage stationary vane 401 has a cross-sectional height of 532mm, and the pressure-side profile of the first vane cross section is-4 × 10-5x3-0.004x2-0.677x-9.123, suction profile of first profile cross-section y-1 x 10-5x3-0.012x2-0.765x+22.63；
Specifically, the second vane cross-section of the first-stage stationary vane 401 has a cross-sectional height of 654mm, and the pressure-side vane profile of the second vane cross-section has a pressure-side vane profile of y ═ y-3×10-5x3-0.003x2-0.659x-10.99, and the profile line of the suction profile of the second blade section is-8 x 10-6x3-0.010x2-0.731x+27.75；
Specifically, the third vane cross section of the first-stage stator blade 401 has a cross-sectional height of 837mm, and the pressure surface profile of the third vane cross section is-2 × 10-5x3-0.002x2-0.659x-15.21, suction profile of third profile cross-section is-8 × 10 ═ y-6x3-0.008x2-0.682x+35.98；
Specifically, the first airfoil section of the second stage vane 402 has a section height of 534mm, and the pressure side airfoil profile of the first airfoil section is-9 × 10-5x3-0.009x2-0.712x-6.257, suction profile of first profile cross-section y-9 × 10-5x3-0.018x2-0.691x+21.04；
Specifically, the second vane section of the second-stage stator vane 402 has a cross-sectional height of 676mm, and the pressure-side vane profile of the second vane section is-5 × 10-5x3-0.007x2-0.631x-6.790, suction profile of the second vane section having a vane profile y-6 × 10-5x3-0.013x2-0.596x+26.7；
Specifically, the third airfoil cross-section of the second stage vane 402 has a cross-sectional height of 889 mm; the pressure profile line of the third blade profile section is y-3 × 10-5x3-0.004x2-0.772x-14.95, and the suction profile of the third profile section is-5 × 10-5x3-0.011x2-0.684x+36.02；
Specifically, the first blade profile section of the primary moving blade 501 has a cross-sectional height of 560mm, and the pressure surface profile line of the first blade profile section is-4 × 10 ═ y-6x3-0.002x2-0.150x-14.96, suction profile of first profile cross-section is y ═ 8x 10-6x3-0.004x2-0.102x+47.74；
Specifically, the second blade profile cross-section of the primary moving blade 501 has a height of 664mm, and the pressure surface profile line of the second blade profile cross-section is y＝-4×10-6x3-0.003x2-0.638x-10.33, suction profile of second vane cross-section is-1 × 10-5x3-0.007x2-0.592x+41.57；
Specifically, the third blade profile section of the primary rotor blade 501 has a section height of 872mm, and the pressure surface profile of the third blade profile section is y 3 × 10-5x3-0.004x2-1.837x-5.573, and the profile of the suction profile of the third profile cross-section is y 5 × 10-5x3-0.009x2-1.899x+26.10；
Specifically, the first blade profile section of the secondary blade 502 has a cross-sectional height of 560mm, and the pressure surface profile of the first blade profile section is-5 × 10 ═ y-6x3-0.002x2-0.118x-18.42, suction profile of first profile cross-section is-1 × 10-5x3-0.004x2-0.070x+49.15；
Specifically, the second blade section of the secondary blade 502 has a section height of 740mm, and the pressure surface profile of the second blade section is y 6 × 10-6x3-0.004x2-1.100x-12.87, suction profile of second blade section is y ═ 5x 10-6x3-0.010x2-1.042x+39.20；
Specifically, the third blade profile of the secondary blade 502 has a cross-sectional height of 920mm, and the pressure surface profile of the third blade profile has a y-3 × 10-5x3-0.003x2-1.994x-8.547, suction profile of third profile cross-section y 3 × 10-5x3-0.009x-1.993x+24.47。
Specifically, the number of blades of the first-stage stator blade 401 is 28, and the number of blades of the second-stage stator blade 402 is 34.
Specifically, the number of blades of the first-stage moving blade 501 is 23, and the number of blades of the second-stage moving blade 502 is 23.
The efficiency of the gas turbine of example 1 was improved by 3% compared to the gas turbine of comparative example 1, as verified by CFD.
Comparative example 1:
this comparative example shows an existing energy-saving gas turbine, which has the same main structure as the two-stage gas turbine in example 1, and as shown in fig. 7 and 8, differs only in that the first-stage stationary blade 401, the second-stage stationary blade 402, the first-stage movable blade 501, and the second-stage movable blade 502 are different. And the first-stage stationary vanes 401 and the second-stage stationary vanes 402 differ in the number of blades.
In the present comparative example, the first vane cross-section of the first-stage stationary blade 401 has a cross-sectional height of 537mm, and the pressure-side profile line of the first vane cross-section is-1 × 10-5x3-0.002x2-0.912x-14.63, suction profile of first profile cross-section y 4 × 10-5x3-0.006x2-1.277x+24.31；
In the present comparative example, the second-vane section of the first-stage stationary blade 401 had a section height of 624mm, and the pressure-side vane profile of the second-vane section was-1 × 10-5x3-0.002x2-0.911x-17.47, suction profile of second vane cross section is y ═ 3 × 10-5x3-0.005x2-1.276x+27.86；
In the present comparative example, the third vane cross-section of the first-stage stationary blade 401 has a cross-sectional height of 843mm, and the pressure-side profile of the third vane cross-section is-5 × 10-6x3-0.001x2-0.915x-24.50, suction profile of third profile cross-section is y-2 × 10-5x3-0.004x2-1.281x+36.94；
In this comparative example, the first airfoil section of the second stage vane 402 has a section height of 522.5mm and the pressure side airfoil profile of the first airfoil section is-4 × 10-55x3-0.005x2-0.721x-7.337, suction profile of first profile cross-section y 3 × 10-5x3-0.014x2-0.813x+24.89；
In this comparative example, the second vane section of the second-stage stationary vane 402 had a cross-sectional height of 717.5mm, and the pressure-side vane profile of the second vane section was-2 × 10-5x3-0.003x2-0.733x-13.91, suction profile of the second vane cross-section y 2 × 10-5x3-0.009x2-0.897x+33.37；
In the present comparative example, the third airfoil cross-section of the second stage vane 402 has a cross-sectional height of 912.5 mm; the pressure profile line of the third blade profile section is y-6 x 10-6x3-0.001x2-0.686x-20.90, suction profile of third profile cross-section is y ═ 1 × 10-5x3-0.006x2-0.872x+41.76；
In this comparative example, the first blade profile section of the primary moving blade 501 had a cross-sectional height of 560mm, and the pressure surface profile line of the first blade profile section was-3 × 10 ═ y-6x3-0.002x2-0.087x-12.49, suction profile of first profile cross-section y-5 x 10-6x3-0.004x2-0.108x+47.20；
In this comparative example, the second-blade profile height of the primary moving blade 501 was 725mm, and the pressure-side profile of the second-blade profile was-9 × 10-6x3-0.002x2-0.901x-15.74, and the profile line of the suction profile of the second vane cross section is y equal to 5 × 10-6x3-0.007x2-0.998x+35.42；
In this comparative example, the third blade profile of the primary rotor blade 501 had a cross-sectional height of 986mm, and the pressure surface profile of the third blade profile was-2 × 10-5x3-0.004x2-2.198x-7.184, suction profile of third profile cross-section y-2 × 10-5x3-0.007x2-2.188x+14.91；
In this comparative example, the structure of the secondary bucket 502 is identical to the structure of the primary bucket 501.
In the present comparative example, the number of blades of the first-stage stator vane is 20, and the number of blades of the second-stage stator vane is 30.
In this comparative example, the number of blades of the first-stage movable blade was 23, and the number of blades of the second-stage movable blade was 23.
Example 2:
the present embodiment presents a vane for a two-stage gas turbine, as shown in fig. 5 and 6, comprising three airfoil sections, respectively a first airfoil section, a second airfoil section and a third airfoil section, each of the first airfoil section, the second airfoil section and the third airfoil section comprising a pressure face airfoil profile and a suction face airfoil profile;
the first profile section of the stator blade has a cross-sectional height of 532mm, and the pressure profile of the first profile section is-4 × 10-5x3-0.004x2-0.677x-9.123, suction profile of first profile cross-section y-1 x 10-5x3-0.012x2-0.765x+22.63；
The second blade section of the stator blade has a section height of 654mm, and the pressure surface profile of the second blade section is-3 × 10-5x3-0.003x2-0.659x-10.99, and the profile line of the suction profile of the second blade section is-8 x 10-6x3-0.010x2-0.731x+27.75；
The third blade profile section of the stator blade has a section height of 837mm, and the pressure surface profile of the third blade profile section is-2 × 10 ═ y-5x3-0.002x2-0.659x-15.21, suction profile of third profile cross-section is-8 × 10 ═ y-6x3-0.008x2-0.682x+35.98。
Example 3:
the present embodiment presents a vane for a two-stage gas turbine, as shown in fig. 5 and 6, comprising three airfoil sections, respectively a first airfoil section, a second airfoil section and a third airfoil section, each of the first airfoil section, the second airfoil section and the third airfoil section comprising a pressure face airfoil profile and a suction face airfoil profile;
the first profile section of the stator blade has a section height of 534mm, and the pressure profile of the first profile section is-9 × 10 ═ y-5x3-0.009x2-0.712x-6.257, suction profile of first profile cross-section y-9 × 10-5x3-0.018x2-0.691x+21.04；
The second blade section of the stator blade has a section height of 676mm, and the pressure surface profile of the second blade section is y-5 × 10-5x3-0.007x2-0.631x-6.790, suction profile of the second vane section having a vane profile y-6 × 10-5x3-0.013x2-0.596x+26.7；
The third blade profile section of the stationary blade has a section height of 889 mm; the pressure profile line of the third blade profile section is y-3 × 10-5x3-0.004x2-0.772x-14.95, and the suction profile of the third profile section is-5 × 10-5x3-0.011x2-0.684x+36.02。
Example 4:
the present embodiment provides a movable blade for a two-stage gas turbine, which includes, as shown in fig. 5 and 6, three blade sections, namely, a first blade section, a second blade section, and a third blade section, each of the first blade section, the second blade section, and the third blade section including a pressure surface blade profile line and a suction surface blade profile line;
the first blade section of the movable blade has a section height of 560mm, and the pressure surface blade profile line of the first blade section is-4 × 10 ═ y-6x3-0.002x2-0.150x-14.96, suction profile of first profile cross-section is y ═ 8x 10-6x3-0.004x2-0.102x+47.74；
The second blade section of the movable blade has a section height of 664mm, and the pressure surface profile of the second blade section is y-4 × 10-6x3-0.003x2-0.638x-10.33, suction profile of second vane cross-section is-1 × 10-5x3-0.007x2-0.592x+41.57；
The third blade profile section of the rotor blade has a section height of 872mm, and the pressure profile line of the third blade profile section is 3 × 10-5x3-0.004x2-1.837x-5.573, and the profile of the suction profile of the third profile cross-section is y 5 × 10-5x3-0.009x2-1.899x+26.10。
Example 5:
the present embodiment provides a movable blade for a two-stage gas turbine, which includes, as shown in fig. 5 and 6, three blade sections, namely, a first blade section, a second blade section, and a third blade section, each of the first blade section, the second blade section, and the third blade section including a pressure surface blade profile line and a suction surface blade profile line;
the first blade section of the movable blade has a section height of 560mm, and the pressure surface blade profile line of the first blade section is-5 × 10 ═ y-6x3-0.002x2-0.118x-18.42, suction profile of first profile cross-section is-1 × 10-5x3-0.004x2-0.070x+49.15；
The second blade section of the movable blade has a section height of 740mm, and the pressure profile of the second blade section is y 6 × 10-6x3-0.004x2-1.100x-12.87, suction profile of second blade section is y ═ 5x 10-6x3-0.010x2-1.042x+39.20；
The third blade section of the movable blade has a section height of 920mm, and the pressure surface profile line of the third blade section is 3 × 10-5x3-0.003x2-1.994x-8.547, suction profile of third profile cross-section y 3 × 10-5x3-0.009x-1.993x+24.47。
Claims (7)
1. A two-stage 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), a movable blade (5) is installed on a hub (3) of the rotating shaft (2), two stages of static blades (4) are sequentially installed on the casing (1) along the axial direction, two 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 two stages of fixed blades (4) are respectively a first stage fixed blade (401) and a second stage fixed blade (402);
the two stages of movable blades (5) are respectively a first-stage movable blade (501) and a second-stage movable blade (502);
the method is characterized in that:
the first-stage static blade (401), the second-stage static blade (402), the first-stage movable blade (501) and the second-stage movable blade (502) respectively comprise three blade-shaped sections which are respectively a first blade-shaped section, a second blade-shaped section and a third blade-shaped section, and each of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section comprises a pressure surface blade-shaped line and a suction surface blade-shaped line;
the first blade profile section of the first-stage stationary blade (401) has the section height of 532mm, and the pressure surface blade profile line of the first blade profile section is-4 multiplied by 10-5x3-0.004x2-0.677x-9.123, suction profile of first profile cross-section y-1 x 10-5x3-0.012x2-0.765x+22.63；
The section height of a second blade section of the first-stage stationary blade (401) is 654mm, and the pressure surface blade profile line of the second blade section is-3 multiplied by 10-5x3-0.003x2-0.659x-10.99, and the profile line of the suction profile of the second blade section is-8 x 10-6x3-0.010x2-0.731x+27.75；
The third blade profile section of the first-stage stator blade (401) has the section height of 837mm, and the pressure surface profile line of the third blade profile section is-2 multiplied by 10-5x3-0.002x2-0.659x-15.21, suction profile of third profile cross-section is-8 × 10 ═ y-6x3-0.008x2-0.682x+35.98；
The section height of a first blade profile section of the second-stage stator blade (402) is 534mm, and the pressure surface blade profile of the first blade profile section is-9 multiplied by 10-5x3-0.009x2-0.712x-6.257, suction profile of first profile cross-section y-9 × 10-5x3-0.018x2-0.691x+21.04；
The second blade section of the second-stage static blade (402) has a section height of 676mm, and the pressure surface profile line of the second blade section is that y is-5 multiplied by 10-5x3-0.007x2-0.631x-6.790, suction profile of the second vane section having a vane profile y-6 × 10-5x3-0.013x2-0.596x+26.7；
The third blade profile section of the second stage stationary blade (402) has a section height of 889 mm; the pressure profile line of the third blade profile section is y-3 × 10-5x3-0.004x2-0.772x-14.95, and the suction profile of the third profile section is-5 × 10-5x3-0.011x2-0.684x+36.02；
The first blade profile section of the first-stage movable blade (501) has the section height of 560mm, and the pressure surface blade profile line of the first blade profile section is-4 multiplied by 10-6x3-0.002x2-0.150x-14.96, suction profile of first profile cross-section is y ═ 8x 10-6x3-0.004x2-0.102x+47.74；
The section height of a second blade section of the first-stage movable blade (501) is 664mm, and the pressure surface blade profile line of the second blade section is-4 multiplied by 10-6x3-0.003x2-0.638x-10.33, suction profile of second vane cross-section is-1 × 10-5x3-0.007x2-0.592x+41.57；
The third blade profile section of the first-stage movable blade (501) has the section height of 872mm, and the pressure surface profile line of the third blade profile section is 3 multiplied by 10-5x3-0.004x2-1.837x-5.573, and the profile of the suction profile of the third profile cross-section is y 5 × 10-5x3-0.009x2-1.899x+26.10；
The section height of a first blade profile section of the secondary movable blade (502) is 560mm, and the pressure surface blade profile line of the first blade profile section is-5 multiplied by 10-6x3-0.002x2-0.118x-18.42, suction profile of first profile cross-section is-1 × 10-5x3-0.004x2-0.070x+49.15；
The section height of a second blade section of the secondary movable blade (502) is 740mm, and the pressure surface blade profile line of the second blade section is y which is 6 multiplied by 10-6x3-0.004x2-1.100x-12.87, suction profile of second blade section is y ═ 5x 10-6x3-0.010x2-1.042x+39.20；
The third blade profile section of the secondary movable blade (502) has the section height of 920mm, and the pressure surface profile line of the third blade profile section is y which is 3 multiplied by 10-5x3-0.003x2-1.994x-8.547, suction profile of third profile cross-section y 3 × 10-5x3-0.009x-1.993x+24.47；
Wherein:
x and y are respectively an abscissa and an ordinate in an Oxyz coordinate system; z is a vertical coordinate in an Oxyz coordinate system;
in an Oxyz coordinate system, the rotation center of the gas turbine where the blade is located is taken as an abscissa x, the height direction of the blade passing through the gravity center of the blade is taken as an ordinate z, the intersection point of the abscissa x and the ordinate z is taken as an origin O, and the direction passing through the origin O and perpendicular to an Oxz plane is taken as an ordinate y.
2. A two-stage gas turbine according to claim 1, wherein the number of blades of the first stage stator vanes (401) is 28 and the number of blades of the second stage stator vanes (402) is 34.
3. The two-stage gas turbine as claimed in claim 1, wherein the number of the first stage moving blades (501) is 23, and the number of the second stage moving blades (502) is 23.
4. A stator blade for a two-stage gas turbine is characterized by comprising three blade-shaped sections, namely a first blade-shaped section, a second blade-shaped section and a third blade-shaped section, wherein each of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section comprises a pressure surface blade-shaped profile and a suction surface blade-shaped profile;
the first blade profile section of the stator blade has a section height of 532mm, and the pressure surface profile line of the first blade profile section is-4 x 10 ═ y-5x3-0.004x2-0.677x-9.123, suction profile of first profile cross-section y-1 x 10-5x3-0.012x2-0.765x+22.63；
The second blade section of the stator blade has a section height of 654mm, and the pressure surface profile of the second blade section is-3 × 10-5x3-0.003x2-0.659x-10.99, and the profile line of the suction profile of the second blade section is-8 x 10-6x3-0.010x2-0.731x+27.75；
The third blade section of the stator blade has a section height of837mm, and the pressure profile line of the third profile section is-2 × 10 ═ y-5x3-0.002x2-0.659x-15.21, suction profile of third profile cross-section is-8 × 10 ═ y-6x3-0.008x2-0.682x+35.98。
5. A stator blade for a two-stage gas turbine is characterized by comprising three blade-shaped sections, namely a first blade-shaped section, a second blade-shaped section and a third blade-shaped section, wherein each of the first blade-shaped section, the second blade-shaped section and the third blade-shaped section comprises a pressure surface blade-shaped profile and a suction surface blade-shaped profile;
the first blade profile section of the stator blade has a section height of 534mm, and the pressure surface profile line of the first blade profile section is-9 x 10 ═ y-5x3-0.009x2-0.712x-6.257, suction profile of first profile cross-section y-9 × 10-5x3-0.018x2-0.691x+21.04；
The second blade section of the stator blade has a section height of 676mm, and the pressure surface profile line of the second blade section is-5 × 10 ═-5x3-0.007x2-0.631x-6.790, suction profile of the second vane section having a vane profile y-6 × 10-5x3-0.013x2-0.596x+26.7；
The height of the section of the third blade-shaped section of the static blade is 889 mm; the pressure profile line of the third blade profile section is y-3 × 10-5x3-0.004x2-0.772x-14.95, and the suction profile of the third profile section is-5 × 10-5x3-0.011x2-0.684x+36.02。
6. A movable vane for a two-stage gas turbine is characterized by comprising three blade profile sections, namely a first blade profile section, a second blade profile section and a third blade profile section, wherein each of the first blade profile section, the second blade profile section and the third blade profile section comprises a pressure surface blade profile line and a suction surface blade profile line;
the first of the moving bladeThe section height of the section of the first blade profile is 560mm, and the pressure surface blade profile line of the section of the first blade profile is-4 multiplied by 10-6x3-0.002x2-0.150x-14.96, suction profile of first profile cross-section is y ═ 8x 10-6x3-0.004x2-0.102x+47.74；
The section height of the second blade section of the movable blade is 664mm, and the pressure surface blade profile line of the second blade section is that y is-4 multiplied by 10-6x3-0.003x2-0.638x-10.33, suction profile of second vane cross-section is-1 × 10-5x3-0.007x2-0.592x+41.57；
The third blade section of the movable blade has a section height of 872mm, and the pressure surface profile line of the third blade section is 3 × 10-5x3-0.004x2-1.837x-5.573, and the profile of the suction profile of the third profile cross-section is y 5 × 10-5x3-0.009x2-1.899x+26.10。
7. A movable vane for a two-stage gas turbine is characterized by comprising three blade profile sections, namely a first blade profile section, a second blade profile section and a third blade profile section, wherein each of the first blade profile section, the second blade profile section and the third blade profile section comprises a pressure surface blade profile line and a suction surface blade profile line;
the section height of the first blade section of the movable blade is 560mm, and the pressure surface blade profile line of the first blade section is-5 multiplied by 10-6x3-0.002x2-0.118x-18.42, suction profile of first profile cross-section is-1 × 10-5x3-0.004x2-0.070x+49.15；
The height of the second blade section of the movable blade is 740mm, and the pressure surface profile line of the second blade section is y equal to 6 multiplied by 10-6x3-0.004x2-1.100x-12.87, suction profile of second blade section is y ═ 5x 10-6x3-0.010x2-1.042x+39.20；
The third blade section of the movable blade has high sectionThe degree is 920mm, the pressure surface profile line of the third profile section is y which is 3 multiplied by 10-5x3-0.003x2-1.994x-8.547, suction profile of third profile cross-section y 3 × 10-5x3-0.009x-1.993x+24.47。
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| CN113605987A (en) * | 2021-09-14 | 2021-11-05 | 西安陕鼓动力股份有限公司 | Two-stage energy recovery gas turbine, stationary blade and movable blade for medium-sized blast furnace |
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