CN115059516A - Wicker-shaped guide vane of power turbine of gas turbine - Google Patents
Wicker-shaped guide vane of power turbine of gas turbine Download PDFInfo
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- CN115059516A CN115059516A CN202210595208.7A CN202210595208A CN115059516A CN 115059516 A CN115059516 A CN 115059516A CN 202210595208 A CN202210595208 A CN 202210595208A CN 115059516 A CN115059516 A CN 115059516A
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- 239000000203 mixture Substances 0.000 description 6
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- 238000005457 optimization Methods 0.000 description 3
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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
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/141—Shape, i.e. outer, aerodynamic form
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Abstract
The invention provides a wicker-shaped guide vane of a power turbine of a gas turbine, which is a wicker-like guide vane of the power turbine with a slender blade body. The invention aims to provide a guide vane which can effectively reduce the flow loss of a blade profile, improve the aerodynamic performance of a turbine blade, weaken the exciting force caused by wake flow and prolong the service life of a downstream movable blade. Thereby solve prior art and be difficult to further promote turbine efficiency, and the excitation that the wake flow arouses is difficult to reduce, problem that moving vane blade reliability is poor. The invention is used for improving the aerodynamic performance of the turbine blades of the combustion drive compressor unit and the ship gas turbine and weakening the excitation force caused by wake flow.
Description
Technical Field
The invention relates to a wicker-shaped guide vane of a gas turbine power turbine, in particular to a wicker-shaped guide vane of a gas turbine power turbine, which has a slender blade body, is similar to a wicker, has small blade-shaped flow loss and small exciting force caused by wake flow.
Background
The gas turbine has the advantages of high power density, high starting speed and the like, and is widely applied to power generation, fuel drive compression of industrial and offshore platforms and used as a main power device of ships. The efficiency of modern gas turbines reaches a higher level, and the difficulty in further improving the efficiency of units and parts is higher. Further, the gas turbine is a vane-type rotary machine, and the inside thereof is three-dimensional unsteady flow, and unsteady flow caused by factors such as a vane wake affects the acting force on the vane, thereby causing unsteady vibration of the vane. When the aerodynamic frequency is equal to the natural frequency of the blade, the blade resonates, which may result in reduced blade life and even blade damage.
In recent years, with continuous progress of design technology and continuous development of computational fluid mechanics, a full three-dimensional optimization design means is continuously applied in a turbine pneumatic design process, unsteady computation and design technology represented by a closing effect (time sequence effect) plays a great role in improving turbine efficiency, a turbine pneumatic design system, design means and method are continuously enriched and perfected, the improvement of turbine pneumatic performance is continuously promoted by advanced design technology and blade shapes, and the shape of a turbine blade is also developed from a traditional straight blade to complex shapes such as a twisted blade, a twisted swept blade and the like. In addition, for avoiding turbine blade resonance, improve turbine blade's structural reliability, at domestic and foreign student's turbine blade shroud structural optimization, turbine blade flange and stretch a damping structural design, a large amount of research works have been carried out in the aspect of turbine blade frequency modulation etc. effectively improved turbine blade's structural reliability.
In order to meet the requirements of energy conservation and emission reduction, the performance of modern gas turbines is continuously improved, the aerodynamic performance of the turbines is required to be continuously improved, and the flow loss of turbine blades is continuously reduced. However, advanced optimization design techniques based on conventional turbine blades have difficulty in further improving turbine aerodynamic performance. In order to meet the requirement of performance improvement, the shape of the turbine blade is more complex, the full three-dimensional characteristic is more obvious, great influence is caused on the structural reliability of the engine, and the problem of turbine blade vibration is particularly easily caused.
Although scholars and researchers at home and abroad have carried out a lot of researches on the aspects of high-performance turbine aerodynamic design and unsteady flow, and have certain knowledge on improving the turbine aerodynamic performance and revealing unsteady flow in a turbine blade cascade, the researches do not pay attention to how to reduce the unsteady acting force of the blade caused by the wake while improving the turbine blade aerodynamic performance, and there are also few reports on the aspects of improving the turbine aerodynamic performance and weakening the unsteady acting force caused by the wake by adopting a wicker blade type blade structure. Researchers desire an advanced blade profile that improves turbine blade performance and effectively attenuates the effects of wakes causing unsteady rotor blade forces.
Disclosure of Invention
The invention aims to provide a blade profile which can effectively reduce the flow loss of the blade profile, improve the aerodynamic performance of a turbine blade, weaken the exciting force caused by wake flow and prolong the service life of the blade. Therefore, the problems that the turbine efficiency is difficult to further improve, the exciting force caused by wake flow is difficult to reduce and the reliability of the blade is poor in the prior art are solved.
The purpose of the invention is realized as follows: a wicker-shaped guide vane of a power turbine of a gas turbine comprises an upper edge plate, wicker blades 1, wicker blades 2 and a lower edge plate, wherein a gas airflow outer flow channel is formed on the inner surface of the upper edge plate, and a gas airflow inner flow channel is formed on the upper surface of the lower edge plate; the wicker blades 1 and 2 are arranged between the inner flow channel and the outer flow channel of the gas flow and are connected with the upper edge plate and the lower edge plate; the molded lines of the wicker blades 1 and the wicker blades 2 are the same in structure, are uniformly arranged along the circumferential direction, and form the shape of the blade by a pressure surface and a suction surface; the pressure surface of the wicker blade 1 and the suction surface of the wicker blade 2 form a cascade flow channel, and the inner surface of the upper edge plate, the upper surface of the lower edge plate, the pressure surface of the wicker blade 1 and the suction surface of the wicker blade 2 form a blade gas channel.
Furthermore, the upper edge plate, the wicker blade 1, the wicker blade 2 and the lower edge plate are sequentially connected into a whole from top to bottom.
Furthermore, the included angle (A) between the stacking axes of the wicker leaves 1 and 2 is 12 degrees.
Further, the front part of the profile of the wicker blade 1 and the profile of the wicker blade 2 is slightly flat near the front edge, the middle and the rear part are relatively flat, and the integral leaf is in a slender structure and is similar to a bent and hanging wicker.
Furthermore, the chord length of the wicker leaf type is 210 mm.
Further, the axial chord length of the wicker leaf profile is 110 mm.
Furthermore, the radius of the front edge of the wicker leaf profile is 2.5mm, and the ratio of the thickness of the front edge to the chord length is 2.3%.
Furthermore, the radius of the tail edge of the wicker leaf profile is 0.5mm, and the ratio of the thickness of the tail edge to the chord length is 0.48%.
Furthermore, the maximum thickness of the wicker leaf profile is 10.5mm, and the ratio of the maximum thickness to the chord length is 5%.
Further, the number of the leaf of the wicker leaf type over the entire circumference was 30.
Compared with the prior art, the invention has the beneficial effects that: on the basis of fully considering the traditional turbine blade of the gas turbine and aiming at the structural characteristics of the wide-chord turbine blade, the slender characteristic of the wicker is applied to the wide-chord turbine blade, a blade profile which is similar to the slender and uniform thickness of the wicker is constructed, the rear loading characteristic of the blade is more obvious, the adverse pressure gradient section and the adverse pressure gradient are smaller, the blade profile has strong adaptability to the variable working condition, and the width of the wake of the blade is narrowed, so that the flow loss of the blade profile is reduced, and the pneumatic efficiency of the turbine is improved. The slender wicker leaf type has the advantages that the wake of the leaf is narrowed, and the exciting force caused by wake flow is weakened; in addition, compared with the traditional turbine blade profile, the turbine blade profile has longer chord length and stronger control capability on the flow, so that the number of the blades is greatly reduced, the number of the wake is reduced, the exciting force caused by the wake flow is further weakened, and the stress state of the downstream movable blade is improved. Compared with the traditional turbine blade, the turbine blade of the invention can reduce the number of blades by 70 percent, reduce the loss of blade profiles by 1 percent and reduce the total width of wake by 70 percent.
Drawings
FIG. 1 is a schematic view of the gas turbine power turbine blade configuration of the present invention;
FIG. 2 is a schematic view of a gas turbine power turbine cascade flowpath of the present invention;
FIG. 3 is a schematic illustration of a wicker-leaf profile of a gas turbine power turbine blade according to the present invention;
FIG. 4 is a schematic view of a conventional gas turbine power turbine blade profile;
FIG. 5 is a schematic illustration of a wicker-blade profile pressure distribution for a gas turbine power turbine blade according to the present invention;
FIG. 6 is a schematic view of a conventional gas turbine power turbine blade profile pressure distribution.
Detailed Description
The present invention will be described in further detail with reference to the accompanying drawings and specific embodiments.
The first embodiment is as follows: the present embodiment is described with reference to fig. 1 and fig. 2, and a wicker-shaped guide vane of a gas turbine power turbine of the present embodiment includes an upper edge plate 1, a wicker blade 2-2, and a lower edge plate 3, wherein an inner surface 4 of the upper edge plate 1 forms a gas flow outer flow passage 5, and an upper surface 6 of the lower edge plate 3 forms a gas flow inner flow passage 7; the wicker blades 2-1 and 2-2 are arranged between the gas flow inner flow channel 7 and the gas flow outer flow channel 5 and are connected with the upper edge plate 2 and the lower edge plate 3, the molded lines of the wicker blade 2-1 and the wicker blade 2-2 are the same in structure and are uniformly arranged along the circumferential direction, and the pressure surface 8 and the suction surface 9 form the shape of the blade; the pressure surface of the wicker blade 2-1 and the suction surface of the wicker blade 2-2 form a cascade flow channel, and the inner surface 4 of the upper edge plate 1, the upper surface 6 of the lower edge plate 3, the pressure surface 8 of the wicker blade 2-1 and the suction surface 9 of the wicker blade 2-2 form a blade gas channel.
The second embodiment is as follows: the present embodiment is described with reference to fig. 1, and the included angle (a) between the stacking axes of the wicker blades 2-1 and 2-2 of the present embodiment is 12 degrees, so that the number of blades in the entire circumference can be reduced, and the number of wake in the entire circumference can be reduced, compared with a conventional gas turbine power turbine.
Other components and connections are the same as in the first embodiment.
The third concrete implementation mode: referring to fig. 3 and 4, the wicker blade 2-1 and the wicker blade 2-2 according to the present embodiment are slightly flat near the front edge, straight at the middle and rear portions, and have an elongated overall shape, similar to a bent and hanging wicker. Compared with the blade profile of the power turbine blade of the conventional gas turbine, the blade profile is slender, and the cascade flow channel formed by the blade has stronger internal flow control capability, thereby being beneficial to reducing loss.
Other compositions and connections are the same as in the first or second embodiments.
The fourth concrete implementation mode: the wicker-blade-shaped chord length (L) of the present embodiment is 210mm, and the axial chord length (La) of the present embodiment is 110mm, which will be described with reference to fig. 3 to 6. Compared with the blade profile of the power turbine blade of the conventional gas turbine, the blade profile of the power turbine blade of the conventional gas turbine is applied to the wide-chord turbine blade, the blade profile which is similar to a wicker and is slender and uniform in thickness is constructed, the characteristic of rear loading of the blade is more obvious, the adverse pressure gradient section and the adverse pressure gradient are smaller, the blade profile has strong adaptability to variable working conditions, the blade profile has lower flow loss, and the turbine has higher pneumatic efficiency.
Other compositions and connection relationships are the same as in the first, second or third embodiment.
The fifth concrete implementation mode is as follows: in the present embodiment, the leading edge radius (Rle) of the wicker blades 2-1 and 2-2 of the present embodiment is 2.5mm, and the ratio of the leading edge thickness to the chord length is 2.3%. Compared with the blade profile of the power turbine blade of the conventional gas turbine, the radius of the front edge of the blade is not increased, and the ratio of the thickness of the front edge to the chord length is reduced by over 60 percent, so that the blade profile loss is favorably reduced.
Other compositions and connection relationships are the same as those in the first, second, third or fourth embodiment.
The sixth specific implementation mode: in the present embodiment, the tail edge radius (Rte) of the wicker leaves 2-1 and 2-2 of the present embodiment is 0.5mm, and the ratio of the thickness of the tail edge to the chord length is 0.48%, as described with reference to fig. 3 and 4. Compared with the blade profile of the power turbine blade of the conventional gas turbine, the blade profile has the advantages that the radius of the tail edge of the blade is reduced, the ratio of the thickness of the tail edge to the chord length is reduced by more than 60%, the width of the wake of the blade is narrowed, on one hand, the flow loss of the blade profile is reduced, and the aerodynamic efficiency of the turbine is improved; on the other hand, the wake becomes narrow, the pressure fluctuation of the trailing edge is small, the exciting force caused by wake flow is weakened, in addition, the number of blades is greatly reduced, the wake number is reduced, the exciting force caused by wake flow is further weakened, and the stress state of the downstream movable blades is improved.
Other compositions and connection relationships are the same as in the first, second, third, fourth or fifth embodiment.
The seventh embodiment: in the present embodiment, the maximum thickness (Tmax) of the wicker blades 2-1 and 2-2 of the present embodiment is 10.5mm, and the ratio of the maximum thickness to the chord length is 5%, as described with reference to fig. 3 and 4. So set up, compare conventional gas turbine power turbine blade profile, the blade thickness of the utmost point reduces, is favorable to reducing the profile loss, and blade thickness distributes evenly is favorable to improving the blade casting yield simultaneously.
Other compositions and connection relationships are the same as in the first, second, third, fourth, fifth or sixth embodiment.
The specific implementation mode is eight: in the present embodiment, the number of the wicker leaves 2-1 and 2-2 in the present embodiment is 1 to 5, and the total number is 30, as described above with reference to FIG. 1. So set up, compare conventional gas turbine power turbine blade quantity and reduce and exceed 50%, be favorable to reducing turbine blade casting and machining cost, improve whole unit price advantage.
Other compositions and connection relations are the same as those of the first embodiment, the second embodiment, the third embodiment, the fourth embodiment, the fifth embodiment, the sixth embodiment or the fifth embodiment.
The working principle is illustrated by fig. 1-6:
the inner surface 4 of the upper edge plate 1, the upper surface 6 of the lower edge plate 3, the pressure surface 8 of the wicker blade 2-1 and the suction surface 9 of the wicker blade 2-2 form a blade gas channel, the pressure surface 8 of the wicker blade 2-1 and the suction surface 9 of the wicker blade 2-2 form a continuous shrinkage type cascade channel, gas enters the continuous shrinkage type cascade channel from a channel inlet at the front edge of the blade, the pressure energy is converted into speed in the flowing process of the flow channel, the gas pressure is gradually reduced, the gas speed is gradually increased, and therefore the gas enters a downstream movable blade channel at a high speed and blows the movable blades to rotate to do work. After the wicker type blade is adopted, on one hand, the molded line of the blade is slender and uniform in thickness, the rear loading characteristic of the blade is more obvious, the adverse pressure gradient section and the adverse pressure gradient are smaller, the working condition change adaptability of the blade is strong, and the width of the wake of the blade is narrowed, so that the flow loss of the blade is reduced, and the pneumatic efficiency of the turbine is improved; on the other hand, the wake of the blade is narrowed, the exciting force caused by wake flow is weakened, and in addition, compared with the blade shape chord length of the traditional turbine blade, the blade has stronger flow control capability, so that the number of the blades is greatly reduced, the wake number is reduced, the exciting force caused by wake flow is further weakened, and the stress state of the downstream movable blade is improved.
The present invention is capable of other embodiments and its several details are capable of modifications in various obvious respects, all without departing from the spirit and scope of the present invention.
In summary, the present invention relates to a wicker-like gas turbine power turbine vane having an elongated body. The invention aims to provide a guide vane which can effectively reduce the flow loss of a blade profile, improve the aerodynamic performance of a turbine blade, weaken the exciting force caused by wake flow and prolong the service life of a downstream movable blade. Thereby solve prior art and be difficult to further promote turbine efficiency, and the excitation that the wake flow arouses is difficult to reduce, problem that movable vane blade reliability is poor. The invention is used for improving the aerodynamic performance of the turbine blades of the combustion drive compressor unit and the ship gas turbine and weakening the excitation force caused by wake flow.
Claims (8)
1. A wicker-shaped guide vane of a gas turbine power turbine is characterized in that: the device comprises an upper edge plate (1), wicker blades (1, 2-1), wicker blades (2, 2) and a lower edge plate (3), wherein a gas airflow outer channel (5) is formed on the inner surface (4) of the upper edge plate (1), and a gas airflow inner channel (7) is formed on the upper surface (6) of the lower edge plate (3); the wicker blades 1(2-1) and the wicker blades 2(2-2) are arranged between the gas flow inner runner (7) and the gas flow outer runner (5) and are connected with the upper edge plate (2) and the lower edge plate (3); the pressure surface (8) of the wicker blade 1(2-1) and the suction surface (9) of the wicker blade 2(2-2) form a cascade flow channel, and the inner surface (4) of the upper edge plate (1), the upper surface (6) of the lower edge plate (3), the pressure surface of the wicker blade 1(2-1) and the suction surface of the wicker blade 2(2-2) form a blade gas channel; the molded lines of the wicker blades 1(2-1) and the molded lines of the wicker blades 2(2-2) have the same structure, and are uniformly arranged along the circumferential direction, and the blade shapes are formed by a pressure surface (8) and a suction surface (9).
2. The wicker-shaped guide vane of a gas turbine power turbine according to claim 1, wherein: the included angle (A) between the stacking axes of the wicker leaves 1(2-1) and the wicker leaves 2(2-2) is 12 degrees.
3. The wicker-shaped guide vane of a gas turbine power turbine according to claim 2, wherein: the front parts of the wicker blades 1(2-1) and 2(2-2) are slightly flat near the front edge, the middle parts and the rear parts are flat, and the integral leaf type is in a slender structure and is similar to a bent and hanging wicker.
4. The wicker-shaped guide vane of a gas turbine power turbine according to claim 3, wherein: the chord length of the wicker blade 1(2-1) and the chord length of the wicker blade 2(2-2) are 210mm, and the axial chord length is 110 mm.
5. The wicker-shaped guide vane of a gas turbine power turbine according to claim 4, wherein: the radius of the front edge of the wicker blade 1(2-1) and the radius of the front edge of the wicker blade 2(2-2) are 2.5mm, and the ratio of the thickness of the front edge to the chord length is 2.3%.
6. The wicker-shaped guide vane of a gas turbine power turbine according to claim 5, wherein: the radius of the tail edge of the wicker leaves 1(2-1) and 2(2-2) is 0.5mm, and the ratio of the thickness of the tail edge to the chord length is 0.48%.
7. The wicker-shaped guide vane of a gas turbine power turbine according to claim 6, wherein: the maximum thickness of the wicker leaves 1(2-1) and 2(2-2) is 10.5mm, and the ratio of the maximum thickness to the chord length is 5%.
8. The wicker-shaped guide vane of a gas turbine power turbine according to claim 7, wherein: the number of the leaves of the wicker leaves 1(2-1) and the wicker leaves 2(2-2) in the whole circumference is 15, and the total number is 30.
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| CN202210595208.7A CN115059516A (en) | 2022-05-29 | 2022-05-29 | Wicker-shaped guide vane of power turbine of gas turbine |
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| CN202210595208.7A CN115059516A (en) | 2022-05-29 | 2022-05-29 | Wicker-shaped guide vane of power turbine of gas turbine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116186943A (en) * | 2023-04-23 | 2023-05-30 | 中国航发四川燃气涡轮研究院 | Turbine blade frequency modulation method based on root extension structural parameter adjustment |
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| CN101915130A (en) * | 2010-06-25 | 2010-12-15 | 北京理工大学 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
| CN104895618A (en) * | 2015-04-10 | 2015-09-09 | 中国科学院工程热物理研究所 | Super-high load low pressure turbine blade, high load low pressure turbine and aviation gas turbine engine |
| CN210530928U (en) * | 2019-09-09 | 2020-05-15 | 哈尔滨电气股份有限公司 | First-stage guide vane of power turbine for medium-sized gas turbine |
| CN114282324A (en) * | 2021-12-30 | 2022-04-05 | 段鹏浩 | Blade parametric design method |
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- 2022-05-29 CN CN202210595208.7A patent/CN115059516A/en active Pending
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101915130A (en) * | 2010-06-25 | 2010-12-15 | 北京理工大学 | Three-dimensional nozzle ring vane of variable geometry turbocharger and design method thereof |
| CN104895618A (en) * | 2015-04-10 | 2015-09-09 | 中国科学院工程热物理研究所 | Super-high load low pressure turbine blade, high load low pressure turbine and aviation gas turbine engine |
| CN210530928U (en) * | 2019-09-09 | 2020-05-15 | 哈尔滨电气股份有限公司 | First-stage guide vane of power turbine for medium-sized gas turbine |
| CN114282324A (en) * | 2021-12-30 | 2022-04-05 | 段鹏浩 | Blade parametric design method |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN116186943A (en) * | 2023-04-23 | 2023-05-30 | 中国航发四川燃气涡轮研究院 | Turbine blade frequency modulation method based on root extension structural parameter adjustment |
| CN116186943B (en) * | 2023-04-23 | 2023-06-30 | 中国航发四川燃气涡轮研究院 | Turbine blade frequency modulation method based on root extension structural parameter adjustment |
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Application publication date: 20220916 |