EP0023025A1 - Turbinenschaufel - Google Patents

Turbinenschaufel Download PDF

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Publication number
EP0023025A1
EP0023025A1 EP80104153A EP80104153A EP0023025A1 EP 0023025 A1 EP0023025 A1 EP 0023025A1 EP 80104153 A EP80104153 A EP 80104153A EP 80104153 A EP80104153 A EP 80104153A EP 0023025 A1 EP0023025 A1 EP 0023025A1
Authority
EP
European Patent Office
Prior art keywords
blade
straight line
point
flow passage
turbine blade
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP80104153A
Other languages
English (en)
French (fr)
Other versions
EP0023025B1 (de
Inventor
Takeshi Sato
Akira Uenishi
Norio Yasugahira
Katsukuni Hisano
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Hitachi Ltd
Original Assignee
Hitachi Ltd
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Hitachi Ltd filed Critical Hitachi Ltd
Publication of EP0023025A1 publication Critical patent/EP0023025A1/de
Application granted granted Critical
Publication of EP0023025B1 publication Critical patent/EP0023025B1/de
Expired legal-status Critical Current

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Classifications

    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/301—Cross-sectional characteristics

Definitions

  • the present invention relates to generally a velocity enhancing blade array of axial flow fluid machines and more particularly a turbine blade.
  • a turbine blade profile consists of a plurality of successively merging circular arcs whose radii of curvature are gradually decreased from the leading edge to the trailing edge.
  • Blade profiles are in general designed to obtain a desired inlet angle, a desired outlet angle and a desired blade width or chord length, but hydrodynamical conditions in the flow passage between the adjacent blades are not taken into consideration.
  • understanding of the performance of the blade profiles which can be used in practice is not sufficient. As a result, it has been very difficult to obtain a turbine blade profile which ensures high performance of an axial flow fluid machine.
  • the boundary layers are.formed over the blade surfaces due to the viscosity of the fluid and flow past the outlet of the flow passage, resulting in the lack of velocity of the fluid at the downstream of the outlet.
  • the degree of the lack of the velocity of the fluid at the downstream of the outlet determin ' the performance of the blade profile.
  • the most important factor which must be taken into consideration in design of turbine blade profiles is the thickness of the boundary layer at the outlet of the flow passage between the adjacent blades. In general, the thinner the boundary layer at the outlet, the higher the performance becomes. It has been clarified that the development of the thickness of the boundary layer is closely correlated with the variations in velocity of the fluid passing through the flow passage. However so far the variations in velocity have not been taken into consideration in the design of a flow passage between the blades. As a result, no attempt has been made to suppress the formation of the boundary layer so that the separation of the boundary layer results, causing very serious adverse effects on the performance. Thus it has been difficult to obtain the turbine blade profiles which ensure the high performance.
  • One of the objects of the present invention is therefore to provide a turbine blade which can stabilize the boundary layers thereon, thus ensuring high performance.
  • Another object of the present invention is to provide a high-performance turbine blade which enables the fluid to flow through the flow passage defined between the adjacent turbine blades in such a way that the acceleration of the fluid is almost completed before the fluid reaches the flow direction changing point in the flow passage, whereby the boundary layers can be stabilized and high performance can be ensured.
  • the present invention provides a turbine blade having such a blade profile that (A) a straight line is drawn in such a way that (a) said straight line passes a point of intersection between an extension of a first straight line which, together with a second straight line in parallel with the axis of a circular turbine blade array, defines an inlet angle and an extension of a third straight line which, together with a fourth straight line in parallel with said axis, defines an outlet angle, (b) said straight line is in parallel with said axis and (c) said straight line is spaced apart from the outlet or discharge end of the turbine blade by a distance greater than one half of the chord length thereof; and (B) that at the point of intersection between said straight line thus drawn and the center line of the flow passage defined between the adjacent turbine blades, said point being the flow direction changing point, the smallest width of the flow passage is less than about 0.4 times the width of said flow passage at the inlet thereof, whereby the acceleration of the fluid flowing through the flow passage is almost completed prior to
  • a line H is first drawn which is in parallel with the axis of blades 10 (that is, the direction in which the blades 10 are mounted in a circular array) and which passes the point of intersection J between a first line F inclined with respect to a second line, which is in parallel with the axis of a circular turbine blade array, at an inlet angle ⁇ 1 and a third line inclined with respect to a fourth line in parallel with the above-mentioned axis at an outlet angle a 2 .
  • this line H corresponds to the point at which the fluid flow is deflected in direction within the passage between the back surface 10b of the turbine blade 10 and the front surface 10a of the adjacent blade 10.
  • the inlet width of this passage is denoted by t-while the outlet width, by s.
  • the passage width Sp is the width at the point P at which the center line A of the flow passage intersects the line H.
  • the distance between the straight line H which passes the flow direction changing point P and the outlet of the blade is so selected as to be greater than one half of the chord length C of the blade 10.
  • the portion of the blade profile above the straight line H is referred to as "the upstream portion" while the portion below the straight line H, "the downstream portion".
  • the radius of curvature R N of the upstream portion of the back surface 10b is smaller than that of the prior art blade profile while the radius of curvature R NO of the downstream portion is greater than that of the prior art blade profile.
  • the radius of curvature R NP of the downstream portion of the front surface lOa is greater than that of the prior art blade profile.
  • Fig. 2 shows the development of the flow passage between the adjacent blades along the center line APB shown in Fig. 1. It is seen that the width of the flow passage is drastically reduced at the upstream portion from the inlet to the flow direction changing point P (from A to P in Fig. 1) while the decrease in width is gradual in the downstream portion (from P to B in Fig. 1).
  • the radius of curvature R N of the upstream portion of the back surface lOb (from the inlet to the straight line H in Fig. 1) is made smaller than that of the prior art blade profile. That is, R N /C ⁇ 0.15 in mathematical terms.
  • the radius of curvature R NO of the downstream portion of the back surface 10b (from the straight line H to the outlet in Fig. 1 is expressed by R NO /C > 5.0.
  • the radius of curvature R NP of the downstream portion of the front surface lOa is expressed by R NP /C > 1.3.
  • TABLE 2 shows the relationship between the passage width Sp at the flow direction changing point P, the width S at the outlet and the width t at the inlet. Since the flow passage width at the flow direction changing point P is S P /t ⁇ 0.4, the above width is smaller than that of the prior art blade profile at the upstream of the point P. On the other hand, since the flow passage width at the point P is 0.9 ⁇ S/Sp ⁇ 1.0, the above width is greater than that of the prior art blade profile at the downstream of the point P.
  • the curvature of the back surface above the straight line H, which passes through the flow direction changing point P is made greater while the curvatures of the downstream portions of the front and back surfaces are made smaller or made substantially zero.
  • a flow passage profile can be defined in which an optimum acceleration of flow can be ensured. As a result, the acceleration of the fluid flowing through the flow passage between the blades can be substantially completed before the fluid reaches the flow direction changing point P.
  • the thickness of the blade profile in accordance with the present invention will be described with further reference to Fig. 1.
  • the thickness of the upstream portion of the blade is very noticeably different from that of the prior art blade.
  • the dis - tance d between the straight line F passing the tip E of the blade and the point J and the straight line Q which is in parallel with the straight line F and tangential to the back surface lOb is 1.5 to 2.0 times as compared with the prior art blade.
  • the increase in thickness results from the fact that the redius of curvature R N of the upstream portion of the back surface lOb is reduced so that the upstream portion of the blade is increased in thickness.
  • the acceleration of the fluid can be substantially completed before the fluid reaches the flow direction changing point P without changing the inlet angle ⁇ 1 .
  • the acceleration stabilizes the boundary layers and decreases their thickness.
  • the fluid flow is deflected along the front and back surfaces 10a and lOb, which are concave and convex, respectively, so that satisfactory boundary layers are formed even after passing the flow direction changing point P. As a consequence, a uniform velocity distribution can be attained in the flow-at the downstream of the outlet.
  • the thickness d m of the blade is given by the following dimensionless expression or parameter: where d m is the distance from the point M, at which the straight line Q is tangent to the back surface lOb, to the point at which a straight line constructed at the point M at right angles to the straight line Q intersects the outline profile of the front surface 10a of the blade. It will be apparent that, as compared with the prior art blade in which d m /C is 0.16, the upper portion of the blade is increased in thickness.
  • Fig. 3 shows the flow in the passage between the blades is expressed in terms of the pressure acting on the blade surfaces.
  • the pressure acting on the back surface of the blade has a high pressure drop ⁇ Ps in the upstream portion of the flow passage from the inlet to the point P at which the flow is deflected. Since the pressure drop ⁇ Ps approaches ⁇ P which is a pressure drop in the overall portion of the flow passage, the stabilized boundary layers can be formed.
  • S in Fig. 1 a very gentle increase in pressure is observed while a sudden pressure rise is observed in the case of the prior art blade.
  • a sudden pressure rise (or the decrease in velocity) facilitates the formation of the boundary layers. That is, the pressure rise determines the conditions of the boundary layers formed and consequently the performance of the blade.
  • Fig. 4 Shown in Fig. 4 are the velocity distribution V, displacement thickness ⁇ and momentum thickness 6 on the back surface lOb of the blade.
  • the thicknesses 6 and 0 are the measures in determining the thickness of the boundary layer and are calculated (according to "TN D-5681", published by NASA, May 1970) based upon the pressure distributions shown in Fig. 3.
  • Fig. 5 is shown the relationship between the blade profile loss coefficient e and the inlet and outlet angles a and a 2 .
  • the blade profile loss coefficient e is plotted along the ordinate while the deflection angle [180° - ( ⁇ 1 + a 2 )], along the abscissa. It is seen that when the deflection angle is close to 100°, the blade profile loss coefficient can be made as little as about 0.02 as compared with the prior art blade having a blade profile loss coefficient of higher than 0.025.
  • the present invention provides a blade profile with a minimum loss and a higher degree of performance.
  • the acceleration is almost completed before the flow direction changing point so that the boundary layers can be highly stabilized and consequently the velocity enhancing and high performance blade profile can be provided.

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP19800104153 1979-07-18 1980-07-16 Turbinenschaufel Expired EP0023025B1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
JP90426/79 1979-07-18
JP9042679A JPS5614802A (en) 1979-07-18 1979-07-18 Profile of accelerating blade

Publications (2)

Publication Number Publication Date
EP0023025A1 true EP0023025A1 (de) 1981-01-28
EP0023025B1 EP0023025B1 (de) 1989-03-15

Family

ID=13998272

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19800104153 Expired EP0023025B1 (de) 1979-07-18 1980-07-16 Turbinenschaufel

Country Status (3)

Country Link
EP (1) EP0023025B1 (de)
JP (1) JPS5614802A (de)
DE (1) DE3072147D1 (de)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5108942A (en) * 1987-03-18 1992-04-28 Mitsubishi Denki Kabushiki Kaisha Master slice integrated circuit having a memory region
US5172210A (en) * 1987-03-18 1992-12-15 Mitsubishi Denki Kabushiki Kaisha Master slice integrated circuit having a memory region
WO2007010329A1 (en) * 2005-07-15 2007-01-25 Vestas Wind Systems A/S Wind turbine blade

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5829603U (ja) * 1981-08-21 1983-02-25 芝浦メカトロニクス株式会社 保線機械の車体横振装置
DE3201436C1 (de) * 1982-01-19 1983-04-21 Kraftwerk Union AG, 4330 Mülheim Turbomaschinenschaufel
JPS60250102A (ja) * 1984-05-25 1985-12-10 芝浦メカトロニクス株式会社 コンパクタ付きバラストスイ−パ
JPS61122302A (ja) * 1984-11-20 1986-06-10 芝浦メカトロニクス株式会社 位置調整機能を備えたコンパクタ装置
US4900230A (en) * 1989-04-27 1990-02-13 Westinghouse Electric Corp. Low pressure end blade for a low pressure steam turbine
DE102008031781B4 (de) * 2008-07-04 2020-06-10 Man Energy Solutions Se Schaufelgitter für eine Strömungsmaschine und Strömungsmaschine mit einem solchen Schaufelgitter
JP6396093B2 (ja) 2014-06-26 2018-09-26 三菱重工業株式会社 タービン動翼列、タービン段落及び軸流タービン
US11015993B2 (en) 2019-10-02 2021-05-25 Cnh Industrial America Llc System and method for wirelessly monitoring the operational status of tools of an agricultural implement

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR616250A (fr) * 1925-05-27 1927-01-29 Brown Aubage à réaction
GB550393A (en) * 1941-05-21 1943-01-06 Oscar Anton Wiberg Blade rim for steam or gas turbines
DE1272305B (de) * 1959-01-27 1968-07-11 Siemens Ag Beschaufelung fuer Dampfturbinen
US3475108A (en) * 1968-02-14 1969-10-28 Siemens Ag Blade structure for turbines

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5237526B2 (de) * 1973-04-20 1977-09-22

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR616250A (fr) * 1925-05-27 1927-01-29 Brown Aubage à réaction
GB550393A (en) * 1941-05-21 1943-01-06 Oscar Anton Wiberg Blade rim for steam or gas turbines
DE1272305B (de) * 1959-01-27 1968-07-11 Siemens Ag Beschaufelung fuer Dampfturbinen
US3475108A (en) * 1968-02-14 1969-10-28 Siemens Ag Blade structure for turbines

Non-Patent Citations (6)

* Cited by examiner, † Cited by third party
Title
FRERICHS A.: "Über Gestaltung und Systematik neuerer Schaufelprofile für Dampf- und Gasturbinen", VDI-ZEITSCHRIFT, vol. 93, no. 27, 21 September 1951 (1951-09-21), DÜSSELDORF, DE, pages 872 - 873 *
IMBACH H.E.: "Berechnung der kompressiblen, reibungsfreien Unterschallströmung durch ebene Schaufelgitter", BROWN BOVERI MITTEILUNGEN, vol. 51, no. 12, 12 December 1964 (1964-12-12), BADEN, CH, pages 752 - 761 *
SPECHTENHAUSER A.: "Modern Industrial Turbine Blading", BROWN BOVERI MITTEILUNGEN, vol. 63, no. 6, 6 June 1976 (1976-06-06), BADEN, CH, pages 339 - 346 *
VON OTTO-ADALBERT VON SCHWERDTNER: "Strömungsuntersuchungen an Turbinenschaufeln", SIEMENS ZEITSCHRIFT, vol. 41, 1967, ERLANGEN, DE, pages 113 - 119 *
VON WALDEMAR ZICKUHR: "Ein vereinfachtes Verfahren zur Angenäherten Bestimmung der Dicke der Schaufelprofile von Turbomaschinen", SIEMENS ZEITSCHRIFT, vol. 8, 8 August 1959 (1959-08-08), ERLANGEN, DE, pages 516 - 520 *
VON WALDEMAR ZICKUHR: "Ermittlung der zweckmässigsten Hauptabmessungen von Überdruckdampfturbinen", SIEMENS ZEITSCHRIFT, vol. 5, 5 May 1954 (1954-05-05), ERLANGEN, DE, pages 189 - 196 *

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5108942A (en) * 1987-03-18 1992-04-28 Mitsubishi Denki Kabushiki Kaisha Master slice integrated circuit having a memory region
US5172210A (en) * 1987-03-18 1992-12-15 Mitsubishi Denki Kabushiki Kaisha Master slice integrated circuit having a memory region
WO2007010329A1 (en) * 2005-07-15 2007-01-25 Vestas Wind Systems A/S Wind turbine blade
US8142162B2 (en) 2005-07-15 2012-03-27 Vestas Wind Systems A/S Wind turbine blade
EP1915514B1 (de) 2005-07-15 2015-11-11 Vestas Wind Systems A/S Windturbinen-rotorblatt

Also Published As

Publication number Publication date
EP0023025B1 (de) 1989-03-15
DE3072147D1 (en) 1989-04-20
JPS5614802A (en) 1981-02-13
JPS6259203B2 (de) 1987-12-10

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