CN212054821U - Last-stage moving blade structure and blade group suitable for high-power air turbine - Google Patents
Last-stage moving blade structure and blade group suitable for high-power air turbine Download PDFInfo
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- CN212054821U CN212054821U CN202020416048.1U CN202020416048U CN212054821U CN 212054821 U CN212054821 U CN 212054821U CN 202020416048 U CN202020416048 U CN 202020416048U CN 212054821 U CN212054821 U CN 212054821U
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Abstract
The utility model discloses a last stage moving blade structure and blading suitable for high-power air turbine contains blade body, midbody, blade root and is used for making the blade form the echelonment shroud ring of whole circle interlocking. The shroud ring comprises double working face clamping grooves, the middle upper blade profile is prevented from twisting relative to the blade root in a two-way mode, the short working face is used for inhibiting the twisting and restoring action of centrifugal force on the middle upper blade profile, and the long working face is used for inhibiting air flow excitation generated by air blast under the working condition of empty load or low load, so that the dynamic stress of the blade is reduced; the top view shroud has no gap after the whole circles are interlocked, so that the blast loss generated in the operation process is avoided; the meridian section of the shroud ring is of a step type, and the leakage loss of the blade top can be effectively reduced through a plurality of sealing teeth. The utility model discloses a last stage moving blade has that energy conversion efficiency is high, operational reliability is high, processing technology is simple, convenient assembling is swift, characteristics such as with low costs, is applicable to the compressed air energy storage or other residual pressure waste heat energy recovery system turbines of 40MW and higher power level.
Description
Technical Field
The utility model belongs to axial-flow type impeller machinery relates to an axial-flow type impeller machinery's blade structure, and specifically speaking is a last stage moving blade structure suitable for high-power grade air turbine and contain the blading of this last stage moving blade.
Background
In order to solve the matching problem of the conventional power system in the links of power generation, power transmission and distribution and power utilization and improve the economy and safety of the conventional power system, in recent years, an advanced compressed air energy storage system which has the advantages of high efficiency, environmental friendliness, large-scale application, no geographical position limitation and the like is rapidly developed. Along with the improvement of the power grade of an energy storage system, the mass/volume flow of required high-pressure air is increased, and the exhaust area of an energy storage turbine is larger and larger, so that the length of a last-stage moving blade is increased, the problems of structural stress increase, blade profile twisting and reversion shape increase, blowing loss caused by an irregular shroud band, blade resonance damage and the like caused by the increase of the length of the blade directly influence the energy conversion efficiency and the safety and stability of operation of the turbine, and the problems frequently occur in the development process of thermal power generation, nuclear power generation and industrial dragging steam turbine units.
The compressed air energy storage system has the characteristic of frequent start and stop (starting from a static state to full load operation at least once every day), the turbine blades bear obvious alternating load, and the through-flow air density of the last-stage moving blade under the low-load working condition is far greater than the steam density of the last stage of the turbine, so the blowing effect and the air flow exciting force of the blades are much stronger than that of the last-stage moving blade of the turbine, and higher requirements are provided for the structural design of the last-stage moving blade of the energy storage turbine.
In addition, the exhaust of the compressed air energy storage system turbine directly enters the atmospheric environment, the exhaust pressure and the density are far higher than those of a steam turbine set, and if structures like a shroud-free structure, a shroud-straight seal structure, a shroud-less step seal structure or a shroud-large gap seal structure of a last-stage moving blade of the steam turbine set are adopted, great blade tip leakage loss can be generated, and the energy conversion efficiency of the set and the system is influenced.
Based on above current situation, the utility model provides a last stage moving blade structure and blading suitable for high-power compressed air energy storage turbine through the optimal design to blade body and shroud structure, improves the natural frequency and the aerodynamic efficiency of blade, makes the unit operation more high-efficient, safety.
SUMMERY OF THE UTILITY MODEL
To the above-mentioned shortcoming and not enough of prior art, the utility model provides a last stage moving blade structure and blading suitable for high-power air turbine is applicable to 40MW and higher power level compressed air energy storage or other residual pressure waste heat energy recovery system turbines. Through the optimized design of the blade body and the shroud structure, particularly through designing the shroud structure into a double-working-surface clamping groove, the middle-upper blade profile is prevented from being twisted relative to the blade root in a two-way mode, wherein the short working surface of the clamping groove is used for inhibiting the twisting and restoring effect of centrifugal force on the middle-upper blade profile, and the long working surface of the clamping groove is used for inhibiting the air flow excitation generated by air blast under the working condition of idle load or low load, so that the dynamic stress of the blade is reduced; the full circle of the shroud ring is interlocked without a gap, so that the blast loss generated in the operation process is avoided; the meridian section of the shroud ring is designed to be of a step type, and the leakage loss of the blade top can be effectively reduced through a plurality of sealing teeth. The utility model discloses a final stage moving blade structure can improve the natural frequency of final stage moving blade, reduces the loss of flow and the blade top clearance leakage, makes the aerodynamic efficiency of this blade/impeller higher, and processing technology is simpler, assembles convenient and fast more, and the unit operation is stable safety more, has good application prospect.
In order to achieve the above object, the solution of the present invention is as follows:
a last-stage moving blade structure suitable for a high-power air turbine, comprising a blade body, an intermediate body, a blade root and a shroud, wherein the shroud is arranged at the top end of the blade body, the intermediate body is arranged at the bottom end of the blade body, the blade root is arranged at the bottom of the intermediate body, and the last-stage moving blade is fixed on a turbine hub through the blade root,
the radial outer side surface of the intermediate body and the radial inner side surface of the shroud band are provided with expansion angles larger than zero along the axial direction of the turbine, so that the hub molded line and the casing molded line of the final-stage moving blade runner are both in an expansion shape along the axial direction of the turbine;
one end of the two ends of the shroud ring along the circumferential direction of the turbine is provided with a clamping groove, the other end of the two ends of the shroud ring is provided with a bulge matched with the clamping groove in shape and size, each clamping groove comprises two inclined working faces which are respectively a long working face and a short working face, the long working face is arranged close to the tail edge of the shroud ring, and the short working face is arranged close to the front edge of the shroud ring; each bulge is also provided with a long working surface and a short working surface which are matched with the shapes and the sizes of the two inclined working surfaces of the clamping grooves;
two adjacent last-stage moving blades are interlocked through a clamping groove and a protrusion on a top shroud of each moving blade.
The utility model discloses an among the last stage moving blade structure suitable for high-power air turbine, in order to adapt to energy storage system open cycle, axial exhaust air turbine overall structure characteristics, the wheel hub molded lines, the casing molded lines of last stage moving blade runner all design into the expanding type to reduce the axial velocity of flow of gas vent, reduce the afterspeed loss, also reduced the external diameter of unit size simultaneously, reduced manufacturing cost.
Preferably, the expansion angle θ of the radially outer surface of the intermediate body in the turbine axial direction (i.e., the hub-line expansion angle of the final-stage moving-blade flow path) is set to be larger than the expansion angle θ of the radially outer surface of the intermediate body in the turbine axial direction1The value of the expansion angle theta of the radial inner side surface of the shroud band is 0-15 degrees along the axial direction of the turbine (namely the expansion angle of a casing molded line of a final-stage moving blade runner)2The value is 0-45 degrees, and the sum theta of two expansion angles is satisfied1+θ2≤45°。
The utility model discloses an among the last stage moving blade structure suitable for high-power air turbine, last stage moving blade is from taking the shroud in the both ends along turbine circumference, and one end is provided with the draw-in groove, and the other end is provided with the arch with the shape of draw-in groove and size looks adaptation, and draw-in groove and arch contain the double-inclined working face of mutually supporting for adjacent last stage moving blade passes through draw-in groove/protruding interlocking, has improved the natural frequency of single blade. The short working surface is used for inhibiting the torsional return action of a centrifugal force on the blade profile at the middle upper part, and avoiding the influence on the throat area, the shock wave form, the airflow attack angle, the outlet airflow angle and the like of the blade flow channel due to the change of the blade profile; the long working surface is used for inhibiting airflow shock excitation generated by blast air under the working condition of no load or low load, reducing the dynamic stress of the blade and prolonging the service life of the blade.
Preferably, the two axial step surfaces of the clamping groove are perpendicular to the leading edge line and the trailing edge line of the surrounding belt respectively, or the two axial step surfaces of the clamping groove are intersected with the leading edge line and the trailing edge line of the surrounding belt in an inclined angle, and preferably, the step height difference h of the clamping groove takes the value of 2-15 mm.
In the last-stage moving blade structure applicable to the high-power air turbine, the chord ratio of the last-stage moving blade span is medium (2.0-8.0), the natural frequency is high, and the influence of dynamic stress on the vibration of the blade is small; meanwhile, the shroud ring improves the natural frequency of the grouped blades through interlocking of the double working face clamping grooves, so that the blades can be provided with no tie bars, the processing technology is simpler, the flow channel is smoother, and the pneumatic efficiency is higher.
Preferably, the shroud of the last-stage moving blade is provided with 2-6 stepped sealing steps distributed along the axial direction of the turbine, and each sealing step is provided with a sealing tooth so as to reduce the leakage loss of the blade top clearance airflow. Through the structural design, more sealing teeth can be arranged, and smaller thermal state blade top clearance (less than or equal to 2mm) is adopted, so that the leakage flow is less than 1% of the total flow.
Preferably, the shrouds of the last-stage moving blades are completely interlocked and have no notch along the circumferential direction of the turbine, so that the blast loss generated in the operation process is avoided, and the combined effect is that the isentropic efficiency of the impeller is higher (93-96%).
Preferably, the maximum thickness of the shroud of the last-stage moving blade is not more than 15mm, so that the stress level of the root part of the blade body and the tenon/mortise is low, and the service life of the blade in a frequent start-stop working state is ensured.
Preferably, the blade root of the last-stage moving blade is a fir-tree tenon, so that the bearing capacity is high, the stress level is low, the installation is convenient and quick, and the shroud can be ensured to have large enough interference.
Preferably, the total length of the last-stage moving blade is 650mm, the height of a working part (blade body) is 520mm, the design rotating speed is 3000rev/min, and the hub divergence angle theta is1Is 6 degrees, and the expansion angle theta of the casing2Is 20 deg..
The utility model discloses a last stage moving blade group, include along a plurality of last stage moving blades of circumference even arrangement on wheel hub, its characterized in that, each last stage moving blade all has the utility model discloses an above-mentioned last stage moving blade structure, the top of each last stage moving blade is passed through the shroud and is formed whole circle interlocking.
Compared with the prior art, the utility model discloses an advantage and beneficial effect suitable for high-power turbine's last stage moving blade structure and blading are:
1. the casing and the hub molded line of the final-stage moving blade runner are in the equal-position expansion type, so that the axial flow velocity of an exhaust port can be reduced, the residual speed loss is reduced, the outer diameter size of a unit is reduced, and the manufacturing cost is reduced.
2. The two ends of the blade self-contained shroud along the circumferential direction of the turbine comprise clamping grooves/protruding structures with long and short working faces, the short working faces are used for inhibiting the torsional return effect of centrifugal force on the blade profile at the middle upper part, and the influence on the throat area, the shock wave form, the airflow attack angle, the outlet airflow angle and the like of a blade flow channel due to the change of the blade profile is avoided; the long working face is used for inhibiting air flow excitation generated by blast air under the working condition of no load or low load, so that the dynamic stress of the blade is reduced, the service life of the blade is prolonged, and the operation is more stable and safer. When the blade body is not provided with the lacing wire, the flow channel is smoother, the blade processing and assembling process is simpler, and the pneumatic efficiency is higher.
3. The top view shroud has no gap after the blades are interlocked in a whole circle, so that the shroud does not generate blast loss in the operation process, and the pneumatic efficiency is higher.
4. The shroud ring of the blade is provided with a plurality of stepped sealing steps, and more sealing teeth can be arranged; in addition, the whole quality of notch cuttype shroud is less, can reduce the centrifugal load that the blade root received to and the deformation volume of unit operation in-process blade, make the thermal state top clearance can take value very little, with the leakage quantity in reduction clearance, improve the aerodynamic efficiency of turbine, promote the life of blade.
Drawings
FIG. 1 is a front view of a last stage moving blade of the present invention suitable for use in a high power air turbine;
FIG. 2 is a side view of the last stage moving blade;
FIG. 3 is a top view of the last stage moving blade;
FIG. 4 is a schematic view of profile parameters of a last stage moving blade;
FIG. 5 is a schematic structural diagram of a clamping groove of a shroud of a last stage moving blade, (A) is a schematic diagram of interlocking between two adjacent last stage moving blades through a clamping groove and a protrusion on a shroud at the top of the last stage moving blades, (B) is a schematic diagram of two axial step surfaces of the clamping groove being perpendicular to a leading edge line and a trailing edge line of the shroud, respectively, and (C) is a schematic diagram of two axial step surfaces of the clamping groove intersecting the leading edge line and the trailing edge line of the shroud at an inclined angle;
FIG. 6 is a schematic meridional view of the shroud;
FIG. 7 is a schematic view of the assembly of 5 adjacent blades;
FIG. 8 is a schematic view of a standard, leading, trailing and trailing bucket shroud assembly;
in the figure: the blade comprises a shroud 1, a blade body 2, a midbody 3, a blade root 4, standard moving blades B1 and B5, a first blade B2, a last blade B3 and a second last blade B4.
Detailed Description
In order to make the purpose, technical solution and advantages of the present invention clearer, the following will combine the drawings in the embodiments of the present invention to perform more detailed description on the technical solution in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are only some, but not all embodiments of the invention. The embodiments described below with reference to the drawings are exemplary and intended to be used for explaining the present invention, and should not be construed as limiting the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention. The structure and technical solution of the present invention will be further specifically described below with reference to the accompanying drawings, and an embodiment of the present invention is provided.
The utility model discloses a last stage moving blade structure suitable for high-power air turbine is shown in fig. 1 ~ 8. As can be seen from the figures 1 and 2, the utility model discloses a last stage moving blade for high-power grade air turbine is applicable to 40MW and higher power grade compressed air energy storage or other residual pressure waste heat energy recovery system turbines, by shroud 1, blade body 2, midbody 3, blade root 4 are constituteed, the height value range of blade body 2 is 200 ~ 800mm, shroud 1 sets up the top at blade body 2, midbody 3 sets up the bottom at blade body 2, blade root 4 sets up the bottom at midbody 3, last stage moving blade passes through blade root 4 to be fixed on turbine wheel hub; the radially outer surface of the intermediate body 3 and the radially inner surface of the shroud ring 1 both have an expansion angle greater than zero in the turbine axial direction, and the expansion angle of the radially outer surface of the intermediate body 3 in the turbine axial direction (i.e., the hub-line expansion angle of the final-stage moving blade flow path) θ1The value is 0-15 degrees, and the expansion angle theta of the radial inner side surface of the shroud band 1 along the axial direction of the turbine (namely the expansion angle of a casing molded line of a final-stage moving blade runner)2The value is 0-45 degrees, and the sum theta of two expansion angles is satisfied1+θ2Not more than 45 degrees, hub molded lines, the casing molded lines of last stage moving blade runner are two-way expansion to reduce carminative axial velocity of flow, reduce the excess speed loss, improve the efficiency of unit, also can reduce the external diameter size of unit simultaneously, reduce the size and the manufacturing cost of static parts such as cylinder, nozzle cascade, aiutage. The blade root is fir type, the bearing capacity is strong, the assembly is convenient, and the shroud band is ensured to have enough in the process of convenient installationThe magnitude of interference is sufficient.
As shown in fig. 3, of the two ends of the shroud ring 1 along the circumferential direction of the turbine, one end of the shroud ring is provided with a slot, and the other end of the shroud ring is provided with a protrusion adapted to the shape and size of the slot, each slot includes two inclined working faces, namely a long working face 12 and a short working face 11, wherein the long working face 12 is arranged near the trailing edge of the shroud ring 1, and the short working face 11 is arranged near the leading edge of the shroud ring 1; each bulge is also provided with a long working surface 12 'and a short working surface 11' which are matched with the shapes and the sizes of the two inclined working surfaces of the clamping groove; the adjacent two last-stage moving blades are interlocked through the clamping grooves and the protrusions on the top surrounding bands of the two last-stage moving blades so as to improve the natural frequency of a single blade, and the short working surfaces 11 and 11' matched with the clamping grooves and the protrusions are used for inhibiting the torsional return effect of centrifugal force on the blade profile at the middle upper part of the last-stage moving blade, so that the influence on the throat area, the shock wave form, the airflow attack angle, the outlet airflow angle and the like of a blade flow channel due to the change of the blade profile is avoided; the long working surfaces 12 and 12' which are matched with each other are used for inhibiting the air flow excitation generated by blast air under the working condition of no load or low load, reducing the dynamic stress of the blade and prolonging the service life of the blade. In the two-way interlocking structure of the shroud slots shown in fig. 3, in a static state and an operating state, the shroud interlocking of the adjacent blades enables the blades in a whole circle to be connected into a group, so that the blades have relatively high natural frequency, and the two-way interlocking structure has the advantages that: firstly, the running of the unit is more stable and safer; and secondly, the lacing bar design of the conventional last-stage moving blade can be cancelled, so that an airflow channel is smoother, the pneumatic efficiency of the turbine is improved, and meanwhile, the processing and assembling processes of the blade are simpler. The blade profile adopts a full three-dimensional free vortex pneumatic design and optimization method, and the axial flow velocity, the boundary layer, the secondary flow, the shock wave loss and the residual velocity loss are all very small.
FIG. 4 is a final stage moving blade profile parameter diagram, wherein the total length of the blade is 650mm, the height of the blade body 2 is 520mm, the design rotation speed is 3000rev/min, and the hub divergence angle θ1Is 6 degrees, and the expansion angle theta of the casing2At 20 deg., other geometric parameters of the blade body 2 with different height sections are shown in the following table 1, where B is the axial chord length, B is the actual chord length, t is the pitch, β is the mounting angle, α is1Is the inlet geometric angle, alpha2Is an outletAnd the geometric angle D is the maximum thickness of the section and is the thickness of the air outlet edge of the blade body.
TABLE 1 geometrical parameters of different height sections of the blade
| Relative height of |
0％ | 50％ | 100％ |
| Actual chord length b/mm | 145 | 145 | 140 |
| Setting angle beta/° | 12 | 43 | 65 |
| Inlet geometry angle alpha1/° | 42 | -15 | -64 |
| Outlet geometry angle alpha2/° | -56 | -66.5 | -74 |
| Maximum thickness D/mm | 24 | 16 | 9 |
| Thickness delta mm of air outlet edge | 1.2 | 0.3 | 1.0 |
As shown in fig. 5, (a) is a schematic diagram of interlocking between two adjacent last-stage moving blades through a clamping groove and a protrusion on a top shroud ring thereof, (B) is a schematic diagram of two axial step surfaces of the clamping groove perpendicular to a leading edge line and a trailing edge line of the shroud ring, respectively, an included angle ω between the step surface of the clamping groove and the leading edge line of the shroud ring is 90 °, and (C) is an inclined angle intersection between the two axial step surfaces of the clamping groove and the leading edge line and the trailing edge line of the shroud ring, an included angle ω between the step surface of the clamping groove and the leading edge line of the shroud ring is not equal to 90 °, and preferably, a step height difference h of the clamping groove is 2-15 mm. The clamping groove comprises 11 and 12 working faces, the shroud rings of adjacent blades are contacted through the working faces of the clamping groove to ensure mutual locking, wherein the short working face 11 is used for inhibiting the torsional return action of a centrifugal force on the blade profile at the middle upper part, and avoiding the influence on the throat area, the shock wave form, the airflow attack angle, the outlet airflow angle and the like of a blade flow channel due to the change of the blade profile; the long working face 12 is used for inhibiting air flow shock excitation generated by blast air under the working condition of no load or low load, and reducing the dynamic stress of the blades, so that the unit is safer and more efficient when running under different working condition loads. The working surfaces 11 and 12 are always in a matched state (static state and working state) with a gap of 0-0.05 mm, and the non-working surfaces are in a gap of 0.2-3.0 mm.
FIG. 6 is a meridional view of the shroud, as shown in the figure, the shroud 1 comprises 4 sealing steps 13, the number of corresponding sealing teeth is large, the clearance of the thermal state blade top is designed to be small (less than or equal to 2mm), the leakage amount is small (less than or equal to 1 percent of the total flow amount) in operation, and the isentropic efficiency is high (more than or equal to 93 percent). The maximum thickness of the shroud after turning is generally not more than 15mm, so that the stress level of the blade root and the tenon/mortise is low, and the service life of the blade is ensured.
FIGS. 7 and 8 are schematic assembly views of a standard moving blade B1/B5, a first blade B2, a second last blade B4 and a last blade B3, wherein the first blade, the second last blade and the last blade which are different from the standard moving blade in structure are arranged in a whole circle for convenient installation, blade root tenons are axially arranged in mortises, and a last blade B3 is finally arranged. The meridian plane of the shroud ring is not provided with a sealing step during the assembly of the blade, and the sealing step is turned after the assembly is finished. The top view shroud band has no gap after the whole circles are interlocked, and the blast loss can not be generated during operation, thereby improving the pneumatic efficiency of the impeller.
To sum up, the utility model provides a last stage moving blade suitable for 40MW and more high power level compressed air energy storage or other excess pressure waste heat energy recovery system turbines, the natural frequency of this blade is high, and energy conversion efficiency is high, and stress and dynamic stress level are low, and manufacturing and convenient assembling have good economic nature and operational reliability.
Through above-mentioned embodiment, realized the utility model discloses an aim has effectively. Those skilled in the art will appreciate that the present invention includes, but is not limited to, what is described in the accompanying drawings and the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not to be limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications, both as expressed in the appended claims, which are intended to cover various modifications, equivalent arrangements, and equivalents thereof, without departing from the spirit and scope of the invention as defined by the appended claims.
Claims (8)
1. A last-stage moving blade structure suitable for a high-power air turbine, comprising a blade body, an intermediate body, a blade root and a shroud, wherein the shroud is arranged at the top end of the blade body, the intermediate body is arranged at the bottom end of the blade body, the blade root is arranged at the bottom of the intermediate body, and the last-stage moving blade is fixed on a turbine hub through the blade root,
the radial outer side surface of the intermediate body and the radial inner side surface of the shroud band are provided with expansion angles larger than zero along the axial direction of the turbine, so that the hub molded line and the casing molded line of the final-stage moving blade runner are both in an expansion shape along the axial direction of the turbine;
one end of the two ends of the shroud ring along the circumferential direction of the turbine is provided with a clamping groove, the other end of the two ends of the shroud ring is provided with a bulge matched with the clamping groove in shape and size, each clamping groove comprises two inclined working faces which are respectively a long working face and a short working face, the long working face is arranged close to the tail edge of the shroud ring, and the short working face is arranged close to the front edge of the shroud ring; each bulge is also provided with a long working surface and a short working surface which are matched with the shapes and the sizes of the two inclined working surfaces of the clamping grooves;
two adjacent last-stage moving blades are interlocked through a clamping groove and a protrusion on a top shroud of each moving blade.
2. The last stage moving blade structure of claim 1, wherein the radially outer surface of the intermediate body has an angle of divergence θ in the axial direction of the turbine1The value of the expansion angle theta is 0-15 degrees, and the expansion angle theta of the radial inner side surface of the shroud ring along the axial direction of the turbine2The value is 0-45 degrees, and the sum theta of two expansion angles is satisfied1+θ2≤45°。
3. The last-stage moving blade structure of claim 1, wherein two step surfaces of the slot in the axial direction are perpendicular to the leading edge line and the trailing edge line of the shroud, respectively, or intersect the leading edge line and the trailing edge line of the shroud at an oblique angle.
4. The last stage moving blade structure according to claim 1, wherein the shroud of the last stage moving blade has 2 to 6 stepped sealing steps distributed in the axial direction of the turbine, each sealing step having a sealing tooth provided thereon.
5. The last stage moving blade structure of claim 1 wherein the shrouds of the last stage moving blades are interlocked in their full rings without gaps in the turbine circumferential direction.
6. The last stage moving blade structure of claim 1, wherein the shroud maximum thickness of the last stage moving blade does not exceed 15 mm.
7. The last stage moving blade structure of claim 1 wherein the blade root of said last stage moving blade is a fir tree type dovetail.
8. A final stage moving blade group comprising a plurality of final stage moving blades uniformly arranged on a hub in a circumferential direction, wherein each of the final stage moving blades has a final stage moving blade structure as set forth in any one of claims 1 to 7, and top portions of the final stage moving blades are interlocked with each other in a full circle by a shroud.
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| CN111425260A (en) * | 2020-03-27 | 2020-07-17 | 中国科学院工程热物理研究所 | Last-stage moving blade structure and blade group suitable for high-power air turbine |
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