CN111636927B - Last-stage self-locking moving blade of gas turbine - Google Patents
Last-stage self-locking moving blade of gas turbine Download PDFInfo
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- CN111636927B CN111636927B CN202010461228.6A CN202010461228A CN111636927B CN 111636927 B CN111636927 B CN 111636927B CN 202010461228 A CN202010461228 A CN 202010461228A CN 111636927 B CN111636927 B CN 111636927B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/10—Final actuators
- F01D17/12—Final actuators arranged in stator parts
- F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
- F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The invention discloses a last stage self-locking moving blade of a gas turbine, which comprises: shroud ring, blade body, platform, extended root and blade root; the blade body is a variable cross-section twisted blade, the area of the cross section from the root to the top is gradually reduced, and relative torsion exists between the root section of the blade body and the top section of the blade body; with the maximum thickness (T) of the middle section of the blade body50％) On the basis of the working height of the blade body and the ratio (L/T) of the working height of the blade body to the working height of the blade body50％) 37.92 root axial width to its ratio (W)r/T50％) 11.31, root diameter of profile to its ratio (Φ/T)50％) 99.19, axial Width of the tip to its ratio (W)t/T50％) Is 2.94. The turbine blade of the final-stage gas turbine disclosed by the invention has the characteristics of high pneumatic efficiency, good strength and vibration performance, reasonable overall structural design and convenience in manufacturing and assembling.
Description
Technical Field
The invention relates to the field of turbine blades of ground heavy gas turbines, in particular to a last-stage self-locking moving blade of a gas turbine.
Background
The gas turbine unit has the advantages of light weight, small volume, quick start, convenient control and the like, and is widely applied to a plurality of fields such as naval vessels, generator sets and the like. From the simple cycle of the gas turbine, it is known that the specific power and performance can be improved by increasing the initial temperature of the gas. The turbine blade has the advantages of high position temperature, large enthalpy drop of low-pressure moving blades of the turbine, large centrifugal stress and vibration stress, prominent pneumatic and strength vibration problems, severe working environment and easy failure, so that whether the turbine blade can work safely and reliably plays a vital role in the normal operation of the gas turbine. Moreover, various performance indexes of the blades are important indexes influencing the working efficiency of the gas turbine, the aerodynamic performance of the low-pressure moving blades of the turbine greatly influences the efficiency of the gas turbine, and particularly, outlet airflow parameters of the last-stage moving blades also have important influence on the aerodynamic performance of the exhaust cylinder.
Chinese patent CN110242355A discloses a 645mm last-stage moving blade for industrial steam turbine, which comprises an integrally formed blade body, a blade root and a boss gold drawing device for making the blade form a whole circle self-locking, the molded line of the blade body is a variable cross-section twisted blade, the height H of the blade body is 645mm, the radius Dr of the bottom is 560mm, and the steam exhaust area of the blade body is 3.6m2And the self-locking boss is arranged at the position of the blade body, which is 0.65 relative to the blade height from bottom to top.
In conclusion, in the actual design process, the blade structure more combined with the actual working conditions is needed, and the overall operation stability and the operation efficiency of the turbine are further improved.
Disclosure of Invention
In view of the above, the present invention provides a final stage self-locking moving blade of a gas turbine, which can solve the above problems.
For this purpose, the present invention is implemented by the following technical means.
A gas turbine last stage self-locking moving blade comprising: the shroud ring, the blade body, the platform, the extending root and the blade root; the blade body is a variable cross-section twisted blade, the area of the cross section from the root to the top is gradually reduced, and relative torsion exists between the root section of the blade body and the top section of the blade body;
with the maximum thickness (T) of the middle section of the blade body50％) For reference, the working height of the blade body is compared with the ratio (L/T)50％) 37.92 root axial width to its ratio (W)r/T50％) 11.31, root diameter of profile to its ratio (Φ/T)50％) 99.19, axial width of the tip to its ratio (W)t/T50％) Is 2.94.
Further, the relative blade height of the blade body is monotonically increased from 0% to 100%;
the pitch-chord length ratio (T) of the root section to the tip section of the blade bodybladeThe variation range of the/b) is 0.284-0.964, and the ratio (T) of the pitch to the axial width of the section from the root part of the blade body to the section from the top part of the blade bodybladeThe variation range of/V) is 0.289-2.067, and the ratio (T) of the pitch from the root section to the top section of the blade body to the maximum thickness of the profile sectionbladeThe variation range of/T) is 2.340-11.124, and the ratio of the pitch of the blade root section to the blade top section to the blade profile section area (T)bladeThe variation range of the/A) is 0.026-0.265.
Further, the mounting angle (beta) of the blade bodyy) 78.79-27.25 degrees, the variation range of the inlet angle (alpha) is 59.85-121.96 degrees, and the variation range of the outlet angle (theta) is 31.53-21.47 degrees.
Further, a ratio of a maximum thickness of the profile line to a maximum thickness of a mid-section of the blade body (T/T)50％) Is 1.48 to 0.55.
Further, the ratio of the thickness of the shroud band to the maximum thickness of the mid-section of the blade body (W/T)50％) Is 0.31-0.51, and the ratio of the axial width of the shroud band to the maximum thickness of the middle section of the blade body (B/T)50％) At 3.08, the shroud pressure angle (θ)t) Is 50-55 degrees.
Further, the ratio of the shroud gap of adjacent blades to the maximum thickness (δ) of the mid-section of the blade bodyt/T50％) Is 0 to 0.02.
Further, the shroud ring is of a step-shaped structure, the middle step is of a sealing tooth structure, and the ratio (l/T) of the height of the sealing tooth to the maximum thickness of the middle section of the blade body50％) The thickness ratio (h/T50%) of the sealing tooth width to the maximum thickness of the middle section of the blade body is 0.315-0.385, and the maximum thickness ratio (h/T50%) of the sealing tooth width to the blade body is 0.168-0.205.
Further, of said blade body and said shroudThe transition fillet is of a variable fillet structure, and the radius R of the front edge of the transition fillet11-1.5 mm, and a trailing edge radius R41-1.5 mm, and the fillet radius R of 30-40% area of the pressure surface close to the tail edge36-8 mm, and the radius R of the fillet of the suction surface in the area of 30% -40% close to the front edge26-8 mm, and the rest areas are in smooth transition.
Further, the side surface of the platform is provided with a damping pin slot structure, and the ratio (L) of the length of the damping pin slot structure to the maximum thickness of the middle section of the blade bodyg/T50％) 9.16-10.18, the ratio of the depth to the maximum thickness (s/T) of the middle section of the blade body50％) Is 0.407-0.509, and the ratio (w) of the width of the groove bottom to the maximum thickness of the middle section of the blade body1/T50％) Is 0.356 to 0.458. The damping pin groove structure is arranged as an outward inclined wall surface gradually inclined from the groove opening to the groove bottom, and the inclination angle (alpha) of the outward inclined wall surfaces) Is 6 to 8 degrees.
Further, the blade root is a 5-tooth fir-tree blade root, wedge angle (theta)r) Is 38.5-41.5 degrees, and the ratio (p) of the tooth pitch to the maximum thickness of the middle section of the blade bodyrthe/T50%) is 0.46-0.56, and the ratio (delta) of the throat width of the 1 st tooth to the 5 th tooth to the maximum thickness of the middle section of the blade bodyrand/T50%) is 1.86 to 0.54.
The invention has the following advantages:
the blade is designed by adopting a ternary flow field design technology, has a certain distortion rule along the blade height direction, meets the static strength requirement of the blade, and has good pneumatic performance, the blade body distortion rule is designed according to a ternary flow theory, the distribution rule of each thermal parameter along the blade body is reasonable, and the pneumatic efficiency of the blade can reach 94.2 percent through calculation verification of professional computational fluid dynamics (CFX), Numeca and the like). In addition, the blade profile has enough strength performance, and the airflow bending stress under the design working condition is small. The blade adopts a whole circle of grouped shroud rings, the shroud rings of the blade are attached during working, and the dynamic stress of the blade is greatly reduced. The blade root is a fir-tree blade root, is convenient to assemble and even in bearing, and can ensure that the blade and the rotor are firmly and stably combined, thereby ensuring the safety of the whole blade.
Drawings
FIG. 1 is a front view of the overall construction of the present invention;
FIG. 2 is a schematic view of cross-sectional parameters in a blade body according to the present invention;
FIG. 3 is a schematic representation of the profile characteristic parameters of the present invention;
FIG. 4 is an enlarged view of I and II of FIG. 3;
FIG. 5 is a block diagram of the shroud and adjacent shrouds of the present invention;
FIG. 6 is a sectional view F-F of FIG. 5;
FIG. 7 is a schematic view of the shroud and the gap between adjacent shrouds of the present invention;
FIG. 8 is a schematic view of the body to shroud transition fillet of the present invention;
FIG. 9 is a side elevation view of a damper pin slot of the platform of the present invention;
FIG. 10 is a cross-sectional view of the damping pin slot G-G of FIG. 9;
FIG. 11 is a schematic view of a blade root configuration of the present invention;
FIG. 12 is a comparison of the centrifugal tensile stress of the conventional blade in example 1 of the present invention;
FIG. 13 is a result of a comparative test of bending stress of an air flow in example 1 of the present invention with that of a conventional blade;
FIG. 14 is a result of a comparison test of aerodynamic efficiency with a conventional blade in example 1 of the present invention.
In the figure:
1-a shroud ring; 2-leaf body; 3-a platform; 4-stretching the root; 5-blade root.
Detailed Description
The invention is further described below with reference to FIGS. 1-11;
referring to fig. 1 to 11, the last stage moving blade of the gas turbine described in the present embodiment is composed of a shroud 1, a blade body 2, a platform 3, a root 4 and a blade root 5, and is formed by precision casting from top to bottom. The molded line of the blade body 2 is a twisted blade with a variable cross section, the area of the cross section from the root to the top is gradually reduced, and two adjacent cross sections are twisted relatively; as shown in fig. 2, the maximum thickness T is taken from the middle section of the blade body 250％Taking the height of the blade body 2 as a reference (hereinafter referred to as the reference), and the ratio L/T of the height to the height50％37.92, root axial width to its ratio Wr/T50％11.31, root diameter of molded wire and ratio phi/T thereof50％99.19, axial width of the tip to its ratio Wt/T50％2.94, axial width of root and ratio C/T thereof50％11.98, vane shroud thickness to its ratio W/T50％0.31 to 0.51, the axial width of the shroud and the ratio B/T thereof50％Was 3.08.
Preferably, the blade root 2 is inserted axially into a separate blade root groove during assembly of the blade; the leaf top is a whole circle of grouped surrounding belt 1; the whole blade is loosely assembled, namely the shroud 1 and the shroud 1 of the adjacent blade are separated, and the shroud 1 of the adjacent blade are contacted through torsion recovery in a working state, so that the blades form a whole circle group.
Preferably, as shown in fig. 3 and 4, the blade body relative blade height (ratio of each section height to the blade height) increases monotonically from 0% to 100%, and the pitch-chord length ratio T from the root section of the blade body 2 to the tip section of the blade body 2 is set tobladeThe variation range of/b is 0.284-0.964, and the pitch-to-axial width ratio T from the root section of the blade body 2 to the top section of the blade body 2bladeThe variation range of/V is 0.289-2.067, and the ratio T of the pitch from the root section of the blade body 2 to the top section of the blade body to the maximum thickness of the blade profile sectionbladeThe variation range of/T is 2.340-11.124, and the ratio T of the pitch from the root section of the blade body 2 to the top section of the blade body 2 to the area of the blade profile sectionbladeThe variation range of/A is 0.026-0.265, and the installation angle betayThe variation range of the angle is 78.79 degrees to 27.25 degrees, and the ratio of the maximum thickness of the molded line to the maximum thickness of the middle section of the blade is T/T50％The variation range of the angle is 1.48-0.55, the variation range of the inlet angle alpha is 59.85-121.96 degrees, and the variation range of the outlet angle theta is 31.53-21.47 degrees.
The adjacent blade shroud clearance to reference ratio delta shown in connection with FIGS. 5-7t/T50％0 to 0.02. Pressure angle theta of shroud 1tIs 50-55 degrees. Sealing tooth height to reference ratio l/T50％0.315 to 0.385, width to reference ratio h/T50％Is 0.168 to 0.205.
Shown in a combination 8, the transition fillet of the blade body 2 and the shroud ring 1 is of a variable fillet structure, and the radius R of the front edge11-1.5 mm, and a trailing edge radius R41-1.5 mm, and 30-40% of the area fillet radius R of the pressure surface close to the trailing edge36-8 mm, and the radius R of the fillet of the suction surface is 30-40% of the area close to the front edge26-8 mm, and the rest areas are in smooth transition.
9-10, the side surface of the platform is provided with a damping pin slot structure, and the length of the damping pin slot structure is equal to the reference ratio Lg/T50％9.16 to 10.18, depth to reference ratio s/T50％0.407-0.509, the ratio w of the width of the groove bottom to the reference value1/T50％Is 0.356 to 0.458. The damping pin groove is provided as a camber wall surface gradually inclined from the notch to the groove bottom at an inclination angle alphasIs 6 to 8 degrees.
As shown in FIG. 11, the blade root is a 5 tooth fir tree root with a wedge angle θrIs 38.5 to 41.5 degrees, and the tooth pitch to reference ratio pr/T50％The variation range of (1) is 0.46-0.56, and the ratio delta of the width of the throat part of the 1 st tooth to the throat part of the 5 th tooth to the reference valuer/T50％Is 1.86 to 0.54.
Example 1
Based on the technical scheme, the working height of the blade body 2 is 372.75mm as an example, and the specific parameters of each section of the formed blade body are as follows:
and carrying out comparison test on the vane and the traditional vane under the same working condition, and selecting representative parameters: the centrifugal tensile stress, the airflow bending stress and the aerodynamic efficiency of the blade are comparative indexes, the results shown in figures 12-14 are obtained, the strength vibration and the aerodynamic performance of the traditional blade and the blade of the invention are compared, and the various performances of the invention are obviously superior to those of the traditional blade.
Although the present invention has been described in detail with reference to examples, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted without departing from the spirit and scope of the invention as defined in the appended claims.
Claims (7)
1. A gas turbine last stage self-locking moving blade comprising: the device comprises a shroud band (1), a blade body (2), a platform (3), a root extension (4) and a blade root (5); the blade body (2) is a variable cross-section twisted blade, the area of the cross section from the root to the top is gradually reduced, and relative torsion exists between the root section of the blade body and the top section of the blade body;
characterized in that the maximum thickness (T) is taken as the middle section of the blade body (2)50％) On the basis, the working height of the blade body (2) is equal to the ratio (L/T)50％) 37.92 root axial width to its ratio (W)r/T50％) 11.31, root diameter of profile to its ratio (Φ/T)50％) 99.19, axial width of the tip to its ratio (W)t/T50％) Is 2.94;
the ratio (W/T) of the thickness of the shroud band (1) to the maximum thickness of the middle section of the blade body (2)50％) Is 0.31-0.51, and the ratio (B/T) of the axial width of the shroud band (1) to the maximum thickness of the middle section of the blade body (2)50％) At 3.08, the pressure angle (theta) of the shroud (1)t) Is 50 to 55 degrees;
the ratio (delta) of the gap between the shroud bands of adjacent blades to the maximum thickness of the middle section of the blade body (2)t/T50％) 0 to 0.02;
the shroud ring (1) is of a step-shaped structure, and the middle step is of a seal tooth structure;
the transition fillet of blade body (2) with shroud (1) is the fillet structure that changes, the leading edge radius R of transition fillet11-1.5 mm, and a trailing edge radius R41-1.5 mm, and 30% -40% of the area fillet radius R of the pressure surface close to the trailing edge36-8 mm, and the radius R of the fillet of the suction surface in the area of 30% -40% close to the front edge26-8 mm, and the rest areas are in smooth transition.
2. Blade according to claim 1, characterized in that the blade body (2) increases monotonically from 0% to 100% in relation to the blade height;
the pitch and chord length from the root section of the blade body (2) to the top section of the blade body (2)Ratio (T)bladeThe variation range of the/b) is 0.284-0.964, and the ratio (T) of the pitch to the axial width of the root section of the blade body (2) to the top section of the blade body (2)bladeThe variation range of/V) is 0.289-2.067, and the ratio (T) of the pitch from the root section of the blade body (2) to the top section of the blade body (2) to the maximum thickness of the blade profile sectionbladeThe variation range of/T) is 2.340-11.124, and the ratio (T) of the pitch from the root section of the blade body (2) to the top section of the blade body (2) to the area of the blade profile sectionbladeThe variation range of the/A) is 0.026-0.265.
3. Blade according to claim 2, characterized in that the setting angle (β) of the blade body (2)y) The variation range of the angle is 78.79-27.25 degrees, the variation range of the inlet angle (alpha) is 59.85-121.96 degrees, and the variation range of the outlet angle (theta) is 31.53-21.47 degrees.
4. A blade according to claim 3, characterized in that the ratio of the profile maximum thickness to the mid-section maximum thickness of the blade airfoil (2) (T/T)50％) Is 1.48 to 0.55.
5. Blade according to claim 1, characterized in that the ratio (l/T) of the seal tooth height to the maximum thickness of the mid-section of the blade body (2)50％) 0.315-0.385, and the maximum thickness ratio (h/T50%) of the sealing tooth width to the middle section of the blade body (2) is 0.168-0.205.
6. Blade according to claim 1, characterized in that the platform (3) is flanked by damping pin-and-slot structures, the length of which is related to the maximum thickness ratio (L) of the mid-section of the blade body (2)g/T50％) 9.16-10.18, the ratio of the depth to the maximum thickness (s/T) of the middle section of the blade body (2)50％) Is 0.407-0.509, the ratio (w) of the groove bottom width to the maximum thickness of the middle section of the blade body (2)1/T50％) 0.356 to 0.458; the damping pin groove structure is arranged as an outward inclined wall surface gradually inclined from the groove opening to the groove bottom, and the inclination angle (alpha) of the outward inclined wall surfaces) Is 6 to 8 degrees.
7. Blade according to claim 1, characterized in that the blade root (5) is a 5-tooth fir-tree blade root with a wedge angle (θ)r) Is 38.5 to 41.5 degrees, and the ratio (p) of the tooth pitch to the maximum thickness of the middle section of the blade body (2)rthe/T50%) is 0.46-0.56, and the ratio (delta) of the throat width of the 1 st tooth to the 5 th tooth to the maximum thickness of the middle section of the blade body (2)rand/T50%) is 1.86 to 0.54.
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| CN202010461228.6A CN111636927B (en) | 2020-05-27 | 2020-05-27 | Last-stage self-locking moving blade of gas turbine |
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| CN202010461228.6A CN111636927B (en) | 2020-05-27 | 2020-05-27 | Last-stage self-locking moving blade of gas turbine |
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| CN111636927B true CN111636927B (en) | 2022-07-01 |
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| CN113107683B (en) * | 2021-05-25 | 2022-02-01 | 浙江燃创透平机械股份有限公司 | Wheel disc spigot positioning structure of gas turbine rotor |
| CN114278391B (en) * | 2021-12-29 | 2024-04-19 | 河北国源电气股份有限公司 | Stator blade group for turbine with tight fit installation |
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| JP2010112276A (en) * | 2008-11-07 | 2010-05-20 | Hitachi Ltd | Turbine moving blade structure |
| CN201606119U (en) * | 2009-11-25 | 2010-10-13 | 北京全四维动力科技有限公司 | Large steam turbine last-stage blade |
| CN103510999A (en) * | 2013-09-29 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | Turbine secondary moving blade applicable to heavy-duty gas turbine |
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| CN110566282A (en) * | 2019-10-24 | 2019-12-13 | 哈尔滨汽轮机厂有限责任公司 | 835mm last-stage moving blade suitable for low-load working condition operation |
Family Cites Families (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN100338337C (en) * | 2002-06-07 | 2007-09-19 | 三菱重工业株式会社 | Turbine bucket assembly and its assembling method |
| JP2005233141A (en) * | 2004-02-23 | 2005-09-02 | Mitsubishi Heavy Ind Ltd | Moving blade and gas turbine using same |
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- 2020-05-27 CN CN202010461228.6A patent/CN111636927B/en active Active
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN1352725A (en) * | 1999-10-15 | 2002-06-05 | 株式会社日立制作所 | Turbine rotor vane |
| US6722852B1 (en) * | 2002-11-22 | 2004-04-20 | General Electric Company | Third stage turbine bucket airfoil |
| JP2010112276A (en) * | 2008-11-07 | 2010-05-20 | Hitachi Ltd | Turbine moving blade structure |
| CN201606119U (en) * | 2009-11-25 | 2010-10-13 | 北京全四维动力科技有限公司 | Large steam turbine last-stage blade |
| CN105229262A (en) * | 2013-05-13 | 2016-01-06 | 西门子股份公司 | The corresponding method of blade system and manufacture blade system |
| CN103510999A (en) * | 2013-09-29 | 2014-01-15 | 哈尔滨汽轮机厂有限责任公司 | Turbine secondary moving blade applicable to heavy-duty gas turbine |
| CN109695479A (en) * | 2018-08-22 | 2019-04-30 | 杭州汽轮机股份有限公司 | A kind of high revolving speed high load capacity low-pressure stage movable vane piece of industrial steam turbine |
| CN110566282A (en) * | 2019-10-24 | 2019-12-13 | 哈尔滨汽轮机厂有限责任公司 | 835mm last-stage moving blade suitable for low-load working condition operation |
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| CN111636927A (en) | 2020-09-08 |
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