CN2328790Y - Rear loading static blade for tangential turbine - Google Patents
Rear loading static blade for tangential turbine Download PDFInfo
- Publication number
- CN2328790Y CN2328790Y CN97216546U CN97216546U CN2328790Y CN 2328790 Y CN2328790 Y CN 2328790Y CN 97216546 U CN97216546 U CN 97216546U CN 97216546 U CN97216546 U CN 97216546U CN 2328790 Y CN2328790 Y CN 2328790Y
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- Prior art keywords
- blade
- blade profile
- chord length
- stator
- static
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05B—INDEXING SCHEME RELATING TO WIND, SPRING, WEIGHT, INERTIA OR LIKE MOTORS, TO MACHINES OR ENGINES FOR LIQUIDS COVERED BY SUBCLASSES F03B, F03D AND F03G
- F05B2250/00—Geometry
- F05B2250/30—Arrangement of components
- F05B2250/32—Arrangement of components according to their shape
- F05B2250/322—Arrangement of components according to their shape tangential
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- Turbine Rotor Nozzle Sealing (AREA)
Abstract
The utility model provides rear loading static blades which are mainly used for various impulse type turbines, particularly for a subsonic grade static blade grid of an impulse type steam turbine. The utility model is characterized in that the maximum values of airload which is generated when steam flow acts upon the surfaces of the blades are distributed at the back half parts of static blades. Compared with an old traditional blade grid, the total aerothermodynamic loss of a static blade grid which is composed of the utility model is greatly reduced, and the variable working condition of the static blade grid is obviously improved.
Description
The utility model relates to a kind of all kinds of tangential turbines that are mainly used in, especially for the back loading stator blade of tangential turbine subsonic speed level static cascade.
Turbo machine mainly is meant the energy source and power equipment of classes such as steam turbine, gas turbine and aeroengine with gas expansion working generation power, extensive use in the national economy every field.Tangential turbine accounts for significant proportion in turbo machine, particularly use in the steam turbine in thermal power generation, and impulse steam turbine accounts for over half.
The energy conversion elements of tangential turbine mainly comprises: be fixed on the plurality of rows moving vane on the rotating shaft wheel disc and be fixed on plurality of rows stator blade on the shell partition plates.Stator blade and moving vane arrange at interval, and when high temperature, high pressure, when swiftly flowing gas passes the air-flow path that is formed by stator blade and moving vane, expansion working promotes movable vane and drives the rotating shaft high speed rotating step by step, externally exports mechanical work.
When gas stream is crossed air-flow path, can produce various aerothermodynamics losses, the size of this loss is directly relevant with turbine efficiency.The air-flow path that is made of two row adjacent stator blades and moving vanes is called the level of turbo machine, and in the aerothermodynamics loss of level, stator blade partly accounts for significant proportion.
The passage component that is made of same row's stator blade is called static cascade, stator blade is called blade profile at the sectional shape of a certain radius, zone between two adjacent stator blades is called the static cascade air-flow path, the physical dimension of air-flow path, shape facility and pneumatic thermodynamic property, all depend on the design of blade profile, the design process of blade profile is called moulding.
In known technology, the traditional design technological scheme of stator blade moulding has a lot, uses also very extensively, but from the aerothermodynamics performance, all exists the aerothermodynamics loss bigger to some extent, and to the relatively poor deficiency that waits of airflow direction adaptability.Briefly introduce below in conjunction with accompanying drawing.
Fig. 1 is a kind of blade profile of impulse steam turbine subsonic speed level stator blade, and by its static cascade air-flow path that constitutes.
Fig. 2 is the partial enlarged drawing of Fig. 1.
The blade profile of stator blade 1 illustrated in figures 1 and 2 is formed by connecting by a suction surface 2, pressure side 3, head 4 and 5 four sections line smoothings of an afterbody, and suction surface 2 respectively is one section smoothed curve with pressure side 3, and head 4 and afterbody 5 respectively are one section circular arc line.Form the air-flow path 6 of a contraction between two adjacent blade profiles, gas is with airspeed C
0With airflow direction angle α
0Inlet passage 6 quickens to flow out gradually, enters the movable vane air-flow path then, and the outlet port of air-flow path 6 is the narrowest, is called the O of throat
sThe length of the blade profile string of a musical instrument 7 is called chord length b
s, adjacent blade profile distance along the circumferential direction is called pitch t
s, t
sWith b
sBetween angle be called blade profile established angle β
s, t
s/ b
sThe dense degree of blade is called cascade solidity in the expression leaf grating.Make the incircle of blade profile in the inner any position of blade profile, its diameter D
sBe called blade profile thickness, the line of a series of incenters is called blade profile mean camber line 8 in the blade profile, mean camber line 8 be one section terminal at the string of a musical instrument 7 two ends, the smoothed curve that intermediate portion arches upward, its degree of arching upward is called blade profile camber δ
s
The basic characteristics of gas flow are in the impulse steam turbine subsonic speed level static cascade, and air-flow must quicken to advance by streamwise, produces pressure simultaneously and falls, and at this moment must produce certain pressure difference between blade suction surface 2 and pressure side 3, is also referred to as airload.Pressure difference is very big near the import of the static cascade air-flow path 6 of traditional design, thereby maximum airload is distributed in the front half part of blade, loading stator blade before being called.The preceding air-flow that loads stator blade inlet, under very big pressure difference effect, separate easily with blade surface, cause the loss of bigger aerothermodynamics, especially when airspeed and airflow direction off-design value (being variable working condition), the easier generation of above-mentioned situation.In addition,, also be easy to generate stronger secondary eddy current, further strengthened the aerothermodynamics loss on the three dimensional space by the static cascade that preceding loading stator blade constitutes.
The purpose of this utility model provides a kind of back loading stator blade that is used for static cascade, by changing the regularity of distribution of airload, to improve gas flow situation in the static cascade, improves the off design performance of static cascade simultaneously.
The purpose of this utility model is achieved in that with the stator blade of traditional design and compares, the head thickness that the back loads the stator blade blade profile reduces, maximum ga(u)ge increases, blade profile thickness and camber change mild, maximum camber is moved behind the position, suction surface and pressure side carry out the fairing finishing, select suitable blade profile established angle and cascade solidity, structure static cascade air-flow path.Above-mentioned stator blade moulding, pressure difference reduces near can making the import of static cascade air-flow path, maximum airload position moves on to the blade latter half part backward, blade strengthens airspeed and airflow direction adaptive capacity (being off design performance), be not easy to take place flow separation, particularly the three dimensional space effect that loading characteristic produces behind the stator blade is fairly obvious, can suppress, delays and weaken the generation and the development of blade grid passage secondary eddy current effectively, further reduces the aerothermodynamics loss.
Fig. 1 promptly is the blade profile that loads stator blade behind the utility model, and by the schematic representation of its static cascade air-flow path that constitutes.
Fig. 2 is the partial enlarged drawing of Fig. 1.
Fig. 3 is a kind of blade profile of preceding loading stator blade of typical traditional design, and by the schematic representation of its static cascade air-flow path that constitutes.
Fig. 4 is the blade profile schematic representation that the back loads stator blade.
Fig. 5 is the blade profile schematic representation of the preceding loading stator blade of traditional design.
Fig. 6 is the comparison diagram of the blade profile thickness of two kinds of stator blades along the chord length distribution rule.
Fig. 7 is the comparison diagram of the blade profile camber of two kinds of stator blades along the chord length distribution rule.
Fig. 8 be two kinds on the stator blade Pneumatic pressure and the comparison diagram of the airload regularity of distribution.
Fig. 9 is aerothermodynamics total losses and the adaptive comparison diagram of airflow direction in two kinds of static cascades.
Below in conjunction with accompanying drawing, the technological scheme that the utility model proposes and embodiment's technical characteristics are elaborated.
Fig. 1 and Fig. 2. shown in the utility model after load the blade profile of stator blade 1, and, it is characterized in that blade profile established angle β by the static cascade air-flow path 6 that it constitutes
sBe 38 °～48 °, cascade solidity t
s/ b
sBe 0.54～0.82.
The blade profile of back loading stator blade 1 shown in Figure 4 is characterized in that, the thickness D of blade profile head 4
S1Be chord length b
s5～10%; The thickness of blade profile afterbody 5 is 0.4～0.6 millimeter; Maximum ga(u)ge D
SmaxBe chord length b
s25～30%, D
SmaxBe positioned at blade profile front half part chord length b
s20～30% places; The maximum camber δ of blade profile mean camber line 8
SmaxBe chord length b
s20～25%, δ
SmaxBe positioned at blade profile front half part chord length b
s35～45% places; Blade profile suction surface 2 and pressure side 3 are respectively the fair curves that first derivative is smooth, second dervative is continuous, and this molded lines can make airspeed variance ratio continuously smooth, is not easy to produce flow separation.
The blade profile of the preceding loading stator blade 1 of traditional design shown in Figure 5 is characterized in that, the thickness D of blade profile head 4
S1Be chord length b
s10～20%; Maximum ga(u)ge D
SmaxBe chord length b
s15～20%; The maximum camber δ of mean camber line 8
SmaxBe positioned at blade profile front half part chord length b
s25～35% places; Blade profile suction surface 2 and pressure side 3 are respectively smooth (second dervative the is discontinuous) curves that is formed by connecting by a section or youngster's section circular arc, though that this vane type line is processed is more convenient, are easy to generate bigger gas flow separation losses.
The blade profile thickness Ds of back loading stator blade 1 shown in Figure 6 is along the distribution curve (solid line) of chord length bs, compare with loading stator blade thickness distribution curve (dotted line) before the traditional design, head thickness reduces half, maximum ga(u)ge increases 1/3rd, the blade profile sectional area increases, thereby the also corresponding increase of blade rigid.
The blade profile camber δ of back loading stator blade 1 shown in Figure 7
sAlong chord length b
sDistribution curve (solid line), compare with loading stator blade blade profile camber distribution curve (dotted line) before the traditional design, maximum camber is suitable, but moves behind the maximum camber position, it is milder that camber is changed.
Pneumatic pressure P is along chord length b on the suction surface 2 of back loading stator blade 1 shown in Figure 8
sDistribution curve (below solid line) and pressure side 3 on the distribution curve (top solid line) of Pneumatic pressure P, compare with loading stator blade pressure distribution curve (dotted line) before the traditional design, the back loads the maximum airload F of stator blade
SmaxBe positioned at blade profile latter half part chord length b
s55～75% places, and the maximum airload F of preceding loading stator blade
SmaxThen be positioned at blade profile front half part chord length b
s20～40% places.
Three dimensional space aerothermodynamics total losses coefficient ξ is to airflow direction angle α in the back loading static cascade that back loading stator blade 1 shown in Figure 9 constitutes
0Adaptability curve (solid line), compare with the preceding loading static cascade airflow direction adaptability curve (dotted line) of traditional design, the aerothermodynamics total losses that the back loads static cascade descends 20% relatively, and in the airflow direction angle is 90 ° ± 30 ℃ scopes, ξ is constant for the total losses coefficient, and the preceding loading static cascade of traditional design is at α
0Be beyond 90 ℃ ± 20 ℃ scopes time, the aerothermodynamics performance promptly begins to worsen.
The embodiment of the back loading stator blade that the utility model proposes is the redesign that is used for the large-scale impulse steam turbine subsonic speed of 200MW, 100MW level, adapts with the product structure size, newly-designed stator blade chord length b at different levels
sScope be 42～140 millimeters.The foregoing description has been applied to the renewal technology transformation of the old steam turbine set of large-size thermal power plant, and succeeds.
Claims (1)
- A kind of tangential turbine that is used for, back loading stator blade especially for impulse steam turbine subsonic speed level static cascade, the blade profile that this back loads stator blade (1) is formed by connecting by a suction surface (2), a pressure side (3), a head (4) and (5) four sections line smoothings of an afterbody, two stator blades (1) promptly constitute the static cascade air-flow path (6) of a contraction, it is characterized in that the established angle β s of blade profile is 38 °～48 °; The thickness of blade profile head (4) is 5～10% of chord length; Maximum ga(u)ge is 25～30% of a chord length, and its position is positioned at 20～30% places of chord length at the front half part of blade profile; The maximum camber of blade profile mean camber line (8) is 20～25% of a chord length, and its position is positioned at 35～45% places of chord length at the front half part of blade profile; The solidity of blades of the static cascade air-flow path (6) that is made of stator blade (1) is 0.54～0.82.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN97216546U CN2328790Y (en) | 1997-05-13 | 1997-05-13 | Rear loading static blade for tangential turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN97216546U CN2328790Y (en) | 1997-05-13 | 1997-05-13 | Rear loading static blade for tangential turbine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN2328790Y true CN2328790Y (en) | 1999-07-14 |
Family
ID=33933418
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN97216546U Expired - Lifetime CN2328790Y (en) | 1997-05-13 | 1997-05-13 | Rear loading static blade for tangential turbine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN2328790Y (en) |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102733866A (en) * | 2012-07-09 | 2012-10-17 | 中国科学院工程热物理研究所 | Compact high-load power turbine generator |
| CN103670528A (en) * | 2013-12-20 | 2014-03-26 | 东方电气集团东方汽轮机有限公司 | Loading method for turbine blade |
| CN104729822A (en) * | 2015-01-16 | 2015-06-24 | 中国民航大学 | Turbine blade wake simulating device |
| CN105507955A (en) * | 2015-12-29 | 2016-04-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Transonic guide blade grid design method of high-pressure turbine |
| CN108729958A (en) * | 2018-04-24 | 2018-11-02 | 哈尔滨工程大学 | A kind of reversion variable geometry turbine of the variable stator vane angle with low consistency zero-lift blade profile |
| CN109356666A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | A kind of Blade Design Method of axial-flow turbine big and small blade combination cascade |
| CN113217226A (en) * | 2021-06-02 | 2021-08-06 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
-
1997
- 1997-05-13 CN CN97216546U patent/CN2328790Y/en not_active Expired - Lifetime
Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102733866A (en) * | 2012-07-09 | 2012-10-17 | 中国科学院工程热物理研究所 | Compact high-load power turbine generator |
| CN102733866B (en) * | 2012-07-09 | 2014-06-04 | 中国科学院工程热物理研究所 | Compact high-load power turbine generator |
| CN103670528A (en) * | 2013-12-20 | 2014-03-26 | 东方电气集团东方汽轮机有限公司 | Loading method for turbine blade |
| CN104729822A (en) * | 2015-01-16 | 2015-06-24 | 中国民航大学 | Turbine blade wake simulating device |
| CN104729822B (en) * | 2015-01-16 | 2017-08-11 | 中国民航大学 | A kind of turbine blade wake analogue means |
| CN105507955A (en) * | 2015-12-29 | 2016-04-20 | 中国航空工业集团公司沈阳发动机设计研究所 | Transonic guide blade grid design method of high-pressure turbine |
| CN105507955B (en) * | 2015-12-29 | 2017-03-29 | 中国航空工业集团公司沈阳发动机设计研究所 | A kind of high-pressure turbine transonic speed guide vane Design of Cascade method |
| CN108729958A (en) * | 2018-04-24 | 2018-11-02 | 哈尔滨工程大学 | A kind of reversion variable geometry turbine of the variable stator vane angle with low consistency zero-lift blade profile |
| CN109356666A (en) * | 2018-12-14 | 2019-02-19 | 中国航发沈阳发动机研究所 | A kind of Blade Design Method of axial-flow turbine big and small blade combination cascade |
| CN113217226A (en) * | 2021-06-02 | 2021-08-06 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
| CN113217226B (en) * | 2021-06-02 | 2022-08-02 | 中国航发湖南动力机械研究所 | Paddle-fan-turbine integrated engine |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CX01 | Expiry of patent term |