CN103256251A - Variable-curvature arc equal-thickness plate wing section for fan group - Google Patents
Variable-curvature arc equal-thickness plate wing section for fan group Download PDFInfo
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- CN103256251A CN103256251A CN 201210038403 CN201210038403A CN103256251A CN 103256251 A CN103256251 A CN 103256251A CN 201210038403 CN201210038403 CN 201210038403 CN 201210038403 A CN201210038403 A CN 201210038403A CN 103256251 A CN103256251 A CN 103256251A
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Abstract
The invention relates to a variable-curvature arc equal-thickness plate wing section for a fan group, and particularly to eight high-performance equal-thickness plate wing sections which are designed by applying an advanced pneumatic analysis technology in the aviation technology and aiming at the practical work condition of a fan with a small size, a low rotating speed and a low Reynolds number (generally less than 106). The invention discloses the maximum camber and position of the group of the wing sections; f is the maximum camber; xf is a transverse coordinate value at the maximum camber place of the wing section; C is a chord length; the original point of the coordinate system where the wing section locates is defined as the front edge point of a mean camber line of the wing section; the X-axis is overlapped with a chord line and points from the front edge of the wing section to the back edge of the wing section; and the Y-axis is vertical to the X-axis which points to the bending direction of the middle arc line of the wing section. Under the same work condition, the fan adopting the variable-curvature arc equal-thickness wing section when being compared with the traditional simple equal-thickness wing section fan is better matched with the practical work condition, has greater blowing rate of the fan, lower noise, higher energy efficiency value (the energy efficiency value=blowing rate/power), higher maximum air speed value and uniform air speed.
Description
Technical field
The present invention relates to one group of high performance fan usefulness and wait the slab aerofoil profile, be specifically related to eight and (be generally less than 10 at slow-speed of revolution fan work reynolds' number is low
6) special operation condition and the slab aerofoil profiles such as variable curvature arc that design.
Background technique
Along with the development of industrial technology, the application of slow-speed of revolution fan in resident living and industrial production more and more widely, as domestic electric fan, ventilation fan, cooling fan etc.Yet the vane airfoil profile of traditional slow-speed of revolution fan is the more and more incompatible requirement of pursuing high efficiency, energy-conservation and low noise now.
Fan blade is the critical piece that determines fan performance, and the section shape of blade (aerofoil profile) is the key that determines the fan blade performance.Existing multiple aerofoil profile in the available data document, the aircraft wing aerofoil profile of state-of-the-art aerofoil profile no more than using in the aviation industry wherein, other industrial field is general to adopt existing aviation aerofoil profile, and the research of aerofoil profile is dropped into seldom.But because the difference of service condition, mainly be aspect such as reynolds' number difference (aviation with aerofoil profile work reynolds' number generally greater than 10
6), so adopt existing aviation aerofoil profile to do the fan blade section shape, can not give full play to the aerofoil profile the best use of, simultaneously owing to reasons such as processing cost height, the application of aviation aerofoil profile on small size slow-speed of revolution fan blade is not extensive.To small size slow-speed of revolution fans such as electric fan, idle call cooling fans, in order to simplify manufacturing processing technic, reduce production costs, often employing waits the slab aerofoil profile.The slab aerofoil profile that waits in traditional fan design data can be designed to single circular arc, two circular arc and parabolic shape, but can be for looking into the single circular arc aerofoil profile of having only of usefulness performance curve, so can only select slab aerofoil profiles such as single circular arc in the actual design for use, adopt slab aerofoil profiles such as other form then to have no data available, this has also caused employed slab aerofoil profile and the actual conditions matching of waiting of present small size slow-speed of revolution fan bad, limit the raising of fan efficiency, caused the waste of resource to a certain extent.
Summary of the invention
The present invention is directed to the not good situation of existing slow-speed of revolution fan blade slab aerofoil profile such as employed grade and actual conditions matching, one group of high performance fan slab aerofoil profile such as variable curvature arc is provided, can be good at mating the little special operation condition of slow-speed of revolution fan work reynolds' number, and after being applied on the fan blade, can improve fan efficiency significantly, reduce fan noise.
For realizing above technical purpose, the present invention by the following technical solutions:
The present invention develops slab aerofoil profiles such as high-performance from air-foil research.At first in conjunction with the applying working condition of slow-speed of revolution fan, adopt the aerodynamic analysis technology of aviation industry, design the high performance fan specific aerofoil profile good with fan actual conditions coupling (the non-slab aerofoil profile that waits).Because the main performance of aerofoil profile depends on the shape of its mean camber line to a great extent, especially low speed aerofoil profile, therefore the rule characteristic of the mean camber line of the high performance fans special airfoil that has designed by further research, and through theory analysis, numerical simulation, experimental verification and fan practical application, it is low that the high performance fans special airfoil that aforementioned and actual conditions matching is good is reduced to cost, slab aerofoil profiles such as the high-performance that is easy to process, this aerofoil profile such as slab such as grade is not simple single circular arc or two circular arc, but by the variable curvature curve that discrete point is determined, be referred to as slab aerofoil profiles such as variable curvature camber.
Based on above-mentioned design method, the invention provides one group of slab aerofoil profile such as high performance fan specific variable curvature arc, be specifically related to eight and wait the slab aerofoil profile, difference called after VACA3409, VACA3408, VACA5307, VACA5306, VACA4906, VACA4706, VACA4206, VACA4307 specify as follows:
VACA3409: the ratio f/C=8.60% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=34.1%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝6.451044×10
-5+0.037449·x
0.5+0.567658·x
1.0+0.055890·x
1.5-0.039999·x
2.0+0.005106·x
2.5-0.000309·x
3.0+8.673023×10
-6·x
3.5-1.270182×10
-8·x
4.0；
VACA3408: the ratio f/C=7.62% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=34.3%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.002214+1.028347·x
0.5-1.510615·x
1.0+1.679717·x
1.5-0.742846·x
2.0+0.185627·x
2.5-0.028415·x
3.0+0.002613·x
3.5-0.000132·x
4.0+2.817704×10
-6·x
4.5；
VACA5307: the ratio f/C=6.82% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=52.5%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝-8.947625×10
-5+0.135277·x
0.5+0.019985·x
1.0+0.132302·x
1.5-0.044133·x
2.0+0.007881·x
2.5-0.000848·x
3.0+4.733366×10
-5·x
3.5-1.074541·x
4.0；
VACA5306: the ratio f/C=6.34% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=53.0%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.004442-1.821187·x
0.5+3.660778·x
1.0-2.653587·x
1.5+1.090799·x
2.0-0.264840·x
2.5+0.038999·x
3.0-0.003426·x
3.5+0.000165·x
4.0-3.326018·x
4.5；
VACA4906: the ratio f/C=5.83% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=49.5%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.000263-0.545654·x
0.5+1.182102·x
1.0-0.640250·x
1.5+0.218083·x
2.0-0.042276·x
2.5+0.004570·x
3.0-0.000261·x
3.5+6.099216×10
-6·x
4.0-1.410729×10
-10·x
4.5；
VACA4706: the ratio f/C=5.59% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=46.7%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.000137+0.087579·x
0.5+0.119931·x
1.0+0.081626·x
1.5-0.026752·x
2.0+0.003478·x
2.5-0.000249·x
3.0+7.656884×10
-6·x
3.5-2.277651×10
-8·x
4.0；
VACA4206: the ratio f/C=6.15% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=41.9%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝3.029194×10
-5-0.014874·x
0.5+0.349937·x
1.0-0.013222·x
1.5-0.000213·x
2.0-0.001292·x
2.5+0.000241·x
3.0-2.212214·x
3.5+1.160781×10
-6·x
4.0-2.573264×10
-8·x
4.5；
VACA4307: the ratio f/C=7.08% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=42.8%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝-0.000168+0.366038·x
1.0-0.005591·x
2.0+2.362125×10
-5·x
3.0-7.701702×10
-8·x
4.0+4.735015×10
-10·x
5.0-1.349356×10
-12·x
6.0；
X wherein
fBe the abscissa value at aerofoil profile maximum camber place, the initial point of definition aerofoil profile place system of coordinates is the leading edge point of aerofoil profile, and X-axis overlaps with the string of a musical instrument, and direction is pointed to airfoil trailing edge by the aerofoil profile leading edge, and Y-axis is pointed to the direction of airfoil mean line bending perpendicular to X-axis.
According to above technological scheme, can realize following beneficial effect:
Slab aerofoil profiles such as the special-purpose variable curvature arc of high performance fans of the present invention owing to used aerodynamic analysis technology advanced in the aeronautical technology when design, have been considered simultaneously that slow-speed of revolution fan work reynolds' number is little (to be generally less than 10
6) special operation condition, so compare with original simple slab aerofoil profile fan that waits, the matching of using the fan of slab aerofoil profiles such as variable curvature arc of the present invention and actual conditions is more excellent, under identical service condition, the air quantity of fan of using slab aerofoil profiles such as variable curvature arc of the present invention is bigger, noise is lower, and efficiency value (efficiency value=air quantity/power) is higher, and the maximum wind speed value is higher and wind speed is even.
Description of drawings
Fig. 1 is slab aerofoil profile schematic representation such as variable curvature arc;
Fig. 2 is the mean camber line of VACA3409 aerofoil profile under the plane right-angle coordinate;
Fig. 3 is the mean camber line of VACA3408 aerofoil profile under the plane right-angle coordinate;
Fig. 4 is the mean camber line of VACA5307 aerofoil profile under the plane right-angle coordinate;
Fig. 5 is the mean camber line of VACA5306 aerofoil profile under the plane right-angle coordinate;
Fig. 6 is the mean camber line of VACA4906 aerofoil profile under the plane right-angle coordinate;
Fig. 7 is the mean camber line of VACA4706 aerofoil profile under the plane right-angle coordinate;
Fig. 8 is the mean camber line of VACA4206 aerofoil profile under the plane right-angle coordinate;
Fig. 9 is the mean camber line of VACA4307 aerofoil profile under the plane right-angle coordinate;
Among the figure, 1 is the aerofoil profile leading edge, 2 aerofoil profile upper surfaces, and 3 is airfoil mean line, and 4 is the aerofoil profile lower surface, and 5 is the aerofoil profile string of a musical instrument, and 6 is airfoil trailing edge, f is the aerofoil profile maximum camber, X
fBe the abscissa value at aerofoil profile maximum camber place, C is chord length.
Embodiment
The nonrestrictive one embodiment of the present invention that disclose of accompanying drawing describe technological scheme of the present invention in detail below with reference to accompanying drawing.
One group of high performance fans slab aerofoil profiles such as variable curvature arc of the present invention, its design principle is: at first in conjunction with the applying working condition of slow-speed of revolution fan, adopt the aerodynamic analysis technology of aviation industry, design the high performance fan specific aerofoil profile good with fan actual conditions coupling.Because the main performance of aerofoil profile depends on the shape of its mean camber line to a great extent, especially low speed aerofoil profile, therefore the rule characteristic of the mean camber line of the high performance fans special airfoil that has designed by further research, and through theory analysis, numerical simulation, experimental verification and fan design practical proof, high performance fans special airfoil aforementioned and that the actual conditions matching is good the slab aerofoil profiles such as high-performance variable curvature arc that cost is low, be easy to process have been simplified to, referring to Fig. 1.
According to above-mentioned design principle, the present invention specifically provides slab aerofoil profiles such as the special-purpose variable curvature arc of eight high performance fans, difference called after VACA3409, VACA3408, VACA5307, VACA5306, VACA4906, VACA4706, VACA4206, VACA4307, as follows for specifying of each aerofoil profile:
VACA3409: the ratio f/C=8.60% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=34.1%, referring to Fig. 2, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝6.451044×10
-5+0.037449·x
0.5+0.567658·x
1.0+0.055890·x
1.5-0.039999·x
2.0+0.005106·x
2.5-0.000309·x
3.0+8.673023×10
-6·x
3.5-1.270182×10
-8·x
4.0；
VACA3408: the ratio f/C=7.62% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=34.3%, referring to Fig. 3, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.002214+1.028347·x
0.5-1.510615·x
1.0+1.679717·x
1.5-0.742846·x
2.0+0.185627·x
2.5-0.028415·x
3.0+0.002613·x
3.5-0.000132·x
4.0+2.817704×10
-6·x
4.5；
VACA5307: the ratio f/C=6.82% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=52.5%, referring to Fig. 4, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝-8.947625×10
-5+0.135277·x
0.5+0.019985·x
1.0+0.132302·x
1.5-0.044133·x
2.0+0.007881·x
2.5-0.000848·x
3.0+4.733366×10
-5·x
3.5-1.074541·x
4.0；
VACA5306: the ratio f/C=6.34% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=53.0%, referring to Fig. 5, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.004442-1.821187·x
0.5+3.660778·x
1.0-2.653587·x
1.5+1.090799·x
2.0-0.264840·x
2.5+0.038999·x
3.0-0.003426·x
3.5+0.000165·x
4.0-3.326018·x
4.5；
VACA4906: the ratio f/C=5.83% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=49.5%, referring to Fig. 6, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.000263-0.545654·x
0.5+1.182102·x
1.0-0.640250·x
1.5+0.218083·x
2.0-0.042276·x
2.5+0.004570·x
3.0-0.000261·x
3.5+6.099216×10
-6·x
4.0-1.410729×10
-10·x
4.5；
VACA4706: the ratio f/C=5.59% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=46.7%, referring to Fig. 7, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.000137+0.087579·x
0.5+0.119931·x
1.0+0.081626·x
1.5-0.026752·x
2.0+0.003478·x
2.5-0.000249·x
3.0+7.656884×10
-6·x
3.5-2.277651×10
-8·x
4.0；
VACA4206: the ratio f/C=6.15% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=41.9%, referring to Fig. 8, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝3.029194×10
-5-0.014874·x
0.5+0.349937·x
1.0-0.013222·x
1.5-0.000213·x
2.0-0.001292·x
2.5+0.000241·x
3.0-2.212214·x
3.5+1.160781×10
-6·x
4.0-2.573264×10
-8·x
4.5；
VACA4307: the ratio f/C=7.08% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=42.8%, referring to Fig. 9, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝-0.000168+0.366038·x
1.0-0.005591·x
2.0+2.362125×10
-5·x
3.0-7.701702×10
-8·x
4.0+4.735015×10
-10·x
5.0-1.349356×10
-12·x
6.0；
X wherein
fBe the abscissa value at aerofoil profile maximum camber place, the initial point of definition aerofoil profile place system of coordinates is the leading edge 1 of aerofoil profile, and X-axis overlaps with the string of a musical instrument 5, and direction is pointed to airfoil trailing edge 6 by aerofoil profile leading edge 1, and Y-axis is pointed to the direction of airfoil mean line 3 bendings perpendicular to X-axis.
The chord length of above-mentioned aerofoil profile is 100 o'clock, and the mean camber line coordinate figure of each aerofoil profile satisfies following table:
In engineering reality, after the mean camber line 3 of each aerofoil profile of the present invention is determined, determine reasonably that according to the size of fan and operating conditions the thickness of slab aerofoil profile such as variable curvature arc can obtain the concrete shape of slab aerofoil profiles such as variable curvature arc, if profile thickness is bigger, then the leading edge 1 of aerofoil profile and trailing edge 6 can be done suitable smooth transition processing, to guarantee the smooth leading edge that flows through aerofoil profile 1 and the trailing edge 6 of air-flow.
Claims (2)
1. slab aerofoil profile such as the special-purpose variable curvature arc of one group of high performance fans, be specifically related to eight and wait the slab aerofoil profile, name for these eight aerofoil profiles is respectively VACA3409, VACA3408, VACA5307, VACA5306, VACA4906, VACA4706, VACA4206, VACA4307, it is characterized in that:
VACA3409: the ratio f/C=8.60% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=34.1%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝6.451044×10
-5+0.037449·x
0.5+0.567658·x
1.0+0.055890·x
1.5-0.039999·x
2.0+0.005106·x
2.5-0.000309·x
3.0+8.673023×10
-6·x
3.5-1.270182×10
-8·x
4.0；
VACA3408: the ratio f/C=7.62% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=34.3%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.002214+1.028347·x
0.5-1.510615·x
1.0+1.679717·x
1.5-0.742846·x
2.0+0.185627·x
2.5-0.028415·x
3.0+0.002613·x
3.5-0.000132·x
4.0+2.817704×10
-6·x
4.5；
VACA5307: the ratio f/C=6.82% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=52.5%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝-8.947625×10
-5+0.135277·x
0.5+0.019985·x
1.0+0.132302·x
1.5-0.044133·x
2.0+0.007881·x
2.5-0.000848·x
3.0+4.733366×10
-5·x
3.5-1.074541·x
4.0；
VACA5306: the ratio f/C=6.34% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=53.0%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.004442-1.821187·x
0.5+3.660778·x
1.0-2.653587·x
1.5+1.090799·x
2.0-0.264840·x
2.5+0.038999·x
3.0-0.003426·x
3.5+0.000165·x
4.0-3.326018·x
4.5；
VACA4906: the ratio f/C=5.83% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=49.5%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.000263-0.545654·x
0.5+1.182102·x
1.0-0.640250·x
1.5+0.218083·x
2.0-0.042276·x
2.5+0.004570·x
3.0-0.000261·x
3.5+6.099216×10
-6·x
4.0-1.410729×10
-10·x
4.5；
VACA4706: the ratio f/C=5.59% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=46.7%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝0.000137+0.087579·x
0.5+0.119931·x
1.0+0.081626·x
1.5-0.026752·x
2.0+0.003478·x
2.5-0.000249·x
3.0+7.656884×10
-6·x
3.5-2.277651×10
-8·x
4.0；
VACA4206: the ratio f/c=6.15% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=41.9%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝3.029194×10
-5-0.014874·x
0.5+0.349937·x
1.0-0.013222·x
1.5-0.000213·x
2.0-0.001292·x
2.5+0.000241·x
3.0-2.212214·x
3.5+1.160781×10
-6·x
4.0-2.573264×10
-8·x
4.5；
VACA4307: the ratio f/C=7.08% of the maximum camber f of aerofoil profile and chord length C, the maximum camber position is X
f/ C=42.8%, the definition chord length is 100 o'clock, the equation of airfoil mean line is
y(x)＝-0.000168+0.366038·x
1.0-0.005591·x
2.0+2.362125×10
-5·x
3.0-7.701702×10
-8·x
4.0+4.735015×10
-10·x
5.0-1.349356×10
-12·x
6.0；
X wherein
fBe the abscissa value at aerofoil profile maximum camber place, the initial point of definition aerofoil profile place system of coordinates is the leading edge point of aerofoil profile, and X-axis overlaps with the string of a musical instrument, and direction is by aerofoil profile leading edge sensing airfoil trailing edge, and Y-axis is perpendicular to X-axis and point to the direction of airfoil mean line bending.
2. slab aerofoil profile such as the special-purpose variable curvature arc of one group of high performance fans according to claim 1, it is characterized in that: the chord length of described aerofoil profile is 100, and then the corresponding coordinate figure of the mean camber line of each aerofoil profile satisfies following table:
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| CN 201210038403 CN103256251A (en) | 2012-02-20 | 2012-02-20 | Variable-curvature arc equal-thickness plate wing section for fan group |
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|---|---|---|---|
| CN 201210038403 CN103256251A (en) | 2012-02-20 | 2012-02-20 | Variable-curvature arc equal-thickness plate wing section for fan group |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105257588A (en) * | 2015-11-05 | 2016-01-20 | 江苏大学 | Blade mixed-flow pump with front cover plate and rear cover plate unequal in thickness |
| CN109595200A (en) * | 2019-01-12 | 2019-04-09 | 中山宜必思科技有限公司 | Its centrifugal blower of a kind of centrifugal wind wheel and its manufacturing method and application |
| CN112360811A (en) * | 2020-10-23 | 2021-02-12 | 浙江三新科技有限公司 | Airfoil type design of centrifugal fan blade with high lift-drag ratio |
| CN113623076A (en) * | 2021-09-06 | 2021-11-09 | 中国联合重型燃气轮机技术有限公司 | Heavy gas turbine air inlet cylinder |
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2012
- 2012-02-20 CN CN 201210038403 patent/CN103256251A/en active Pending
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105257588A (en) * | 2015-11-05 | 2016-01-20 | 江苏大学 | Blade mixed-flow pump with front cover plate and rear cover plate unequal in thickness |
| CN109595200A (en) * | 2019-01-12 | 2019-04-09 | 中山宜必思科技有限公司 | Its centrifugal blower of a kind of centrifugal wind wheel and its manufacturing method and application |
| CN112360811A (en) * | 2020-10-23 | 2021-02-12 | 浙江三新科技有限公司 | Airfoil type design of centrifugal fan blade with high lift-drag ratio |
| CN113623076A (en) * | 2021-09-06 | 2021-11-09 | 中国联合重型燃气轮机技术有限公司 | Heavy gas turbine air inlet cylinder |
| CN113623076B (en) * | 2021-09-06 | 2022-07-22 | 中国联合重型燃气轮机技术有限公司 | Heavy gas turbine air inlet cylinder |
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Application publication date: 20130821 |