US3565548A - Transonic buckets for axial flow turbines - Google Patents

Transonic buckets for axial flow turbines Download PDF

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Publication number
US3565548A
US3565548A US793831*A US3565548DA US3565548A US 3565548 A US3565548 A US 3565548A US 3565548D A US3565548D A US 3565548DA US 3565548 A US3565548 A US 3565548A
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Prior art keywords
buckets
blade
transonic
section
axial flow
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Expired - Lifetime
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US793831*A
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Jackson E Fowler
Josef Herzog
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General Electric Co
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General Electric Co
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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

Definitions

  • This invention relates to axial flow steam turbine bucket design for high speed, long buckets wherein the fluid flow conditions at the radially outer portions, especially of the last stage buckets, exceeds the speed of sound.
  • Such buckets are known as transonic buckets because the steam enters at a speed less than that of sound and emerges at supersonic speeds.
  • one object of the present invention is to provide an improved transonic bucket profile which gives improved efficiency in the transition from subsonic to supersonic flow between buckets.
  • Another object of the invention is to provide an improved transonic bucket profile which is of more uniform thickness throughout so as to add strength without sacrifice in aerodynamic design.
  • the single figure of the drawing is a developed view of two adjacent blade cross sections taken near the outer tips of the buckets and looking radially inward.
  • the invention is practiced by arranging adjacent blades so that the blade sections near the outer periphery overlap about A of the total chord length and shaping the blade profiles a convergent-divergent nozzle over the overlapped one-quarter.
  • Each blade profile is characterized by two locations of increased blade thickness, one near the nose and one near the tail section. Over the midsection of the blade profile, the pressure side and suction side are substantially fiat and diverge from one another toward the tail section.
  • each bucket profile such as 2 is divided for the purpose of definition herein into a nose section 3 extending about A of the chord length, a mid-section 4 extending about /2 of the chord length, and a tail section 5 extending the remaining of the chord length.
  • the nose section 3 of one blade overlaps and is roughly coextensive with the tail section 5 of an adjacent bucket.
  • the blades travel in the direction indicated by the arrow.
  • the upper side 6 is the pressure side of the blades while the lower side 7 is the suction side.
  • the point of greatest blade thick ness is indicated at a and is located back from the leading edge 8 by distance I.
  • the contour of the blade profile on both pressure and suction side over the distance I is quasielliptical and has an l/d ratio satisfying the condition:
  • the blade narrows toward a neck 11 at the start of the mid-section 4 of the blade.
  • the suction side in this narrowing cross section is gently concave as indicated at 12.
  • the pressure side and suction side are substantially fiat. It is to be particularly noted also that the flat pressure and suction sides diverge from the relatively narrow neck 11 at the beginning of mid-section 4 to a relatively thick throat portion indicated at its thickest point as t. Throat portion t is located approximately /4 of the chord length along the blade and is so designated because it lies opposite the thickest nose section d to form therewith the throat of a. convergent-divergent nozzle between blades 1, 2.
  • the nose thickness d will be slightly greater than t and in other cases the throat thickness 1 will be slightly greater than a. In either event, however, the two are approximately the same, relative to other parts of the blade.
  • the tail section 5 of the blade profile comprises a relatively flat suction side which is a continuation of the aforementioned flat suction side over the mid-section of the blade.
  • the blade curvature is reversed after passing through the throat portion t and caused to curve gently toward the trailing edge 9 to provide a slightly concave surface on the pressure side.
  • the radius of curvature over this portion, designated 10, should be at least 20 times that of the radius of curvature at the throat section I.
  • the thickest nose portion d of blade 2 is disposed opposite the thickest throat portion 1 of blade 1 and the two together form a convergent-divergent nozzle of transonic flow conditions indicated at I between the dashed lines.
  • Adjacent zone I is a zone II of supersonic flow and zone III of supersonic flow at essentially constant velocity.
  • the radius of curvature of the concave suction side 12 of blade and the radius of curvature of the concave pressure side 10 of blade 1 are both calculated, preferably using the method of characteristics, which is well know to those skilled in the art, to provide optimum flow conditions.
  • One advantage of the foregoing design in having a nose section and a tail section which are substantially the same thickness, is to provide a more symmetrical bucket of greater strength and to allow enough material for shielding against erosion on leading edge at the outer tips. Also, by employing flat profiles over approximately half of the pressure side and approximately 4 of the suction side, simplifications as to blade shaping are introduced.
  • each of said bucket outer portions being shaped to define a blade profile having a rounded nose section, a mid-section and a tail section extending over approximately the first quarter, the middle half and the last quarter of the chord length respectively,
  • said nose section increasing and then decreasing in thickness to provide a first reference point of maximum thickness therein
  • mid-section having substantially fiat sides increasing in thickness throughout its length to provide a second reference point of maximum thickness between the mid-section and tail section
  • said first and second reference points being of approximately the same blade thickness.
  • each of said bucket outer portions being shaped to define a blade profile having a rounded nose section extending over approximately one-quarter of the chord length, a mid-section extending over approximately onehalf of the chord length, and a tail section extending the remaining one-quarter of the chord length,
  • said nose section disposed in overlapping and coextensive relationship with the tail section of an adjacent blade profile
  • said nose section gradually increasing in thickness commencing at the leading edge thereof and then decreasing in thickness
  • mid-section defining substantially flat surfaces on the pressure and suction sides of the profile and also diverging slightly toward the tail section
  • said tail section having a substantially fiat suction side which is a continuation of said mid-section suction side and having a surface on the pressure side which gently converges from a maximum throat thickness to the bucket trailing edge.

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  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

TURBINE BUCKET PROFILES FOR THE TRANSONIC FLUID FLOW REGION AT THE OUTER PORTIONS OF AXIAL FLOW STEAM TURBINE BUCKETS, THE PROFILES BEING CHARACTERIZED BY SUBSTANTIALLY FLAT PRESSURE AND SUCTION SIDES DIVERGING TOWARD THE TRAILING EDGE OVER THE MID-PORTION OF THE PROFILE, THE BUCKETS OVERLAPPING ONE ANOTHER AND SHAPED TO PROVIDE A TRANSONIC AND SUPERSONIC FLOW REGION BETWEEN BUCKETS.

Description

1971 J. E. FOWLER E 1 3,565,543
TRANSONIC BUCKETS FOR AXIAL FLOW TURBINES Filed Jan. 24, 1969 lNVENTORS JACKSON E. FOWLER,
JOSEF HERZOG, BY 40 W THEIR ATTORNEY.
United States Patent O 3,565,548 TRANSONIC BUCKETS FOR AXIAL FLOW TURBINES Jackson E. Fowler, Schenectady, and Josef Herzog, Scotia,
N.Y., assignors to General Electric Company, a corporation of New York Filed Jan. 24, 1969, Ser. No. 793,831 Int. Cl. F01d 5/14 US. Cl. 416-223 5 Claims ABSTRACT OF THE DISCLOSURE Turbine bucket profiles for the transonic fluid flow region at the outer portions of axial flow steam turbine buckets, the profiles being characterized by substantially flat pressure and suction sides diverging toward the trailing edge over the mid-portion of the profile, the buckets overlapping one another and shaped to provide a transonic and supersonic flow region between buckets.
BACKGROUND OF THE INVENTION This invention relates to axial flow steam turbine bucket design for high speed, long buckets wherein the fluid flow conditions at the radially outer portions, especially of the last stage buckets, exceeds the speed of sound. Such buckets are known as transonic buckets because the steam enters at a speed less than that of sound and emerges at supersonic speeds.
Transition from subsonic to supersonic conditions without the loss of etficiency represents a diificult aerodynamic design problem. That which would give a theoretical optimum fiow condition is often impossible to achieve in a practical blade due to thinness of the blade sections near the outer tips of the buckets. Efforts to achieve good transonic profiles are known in the prior art, wherein a conventional subsonic bucket profile (concave on the pressure side and convex on the suction side) has been reversed so that there is a slightly convex curve on the pressure side and slightly concave curve on the suction side. These profiles and a history of the prior art are exemplified in US. Pat. 3,333,817 issued to F. Rhomberg on Aug. 1, 1967. Such prior art blade profiles terminate in a relatively thick trailing edge which is disposed opposite a blunt leading edge of the adjacent blade.
Accordingly, one object of the present invention is to provide an improved transonic bucket profile which gives improved efficiency in the transition from subsonic to supersonic flow between buckets.
Another object of the invention is to provide an improved transonic bucket profile which is of more uniform thickness throughout so as to add strength without sacrifice in aerodynamic design.
DRAWING The single figure of the drawing is a developed view of two adjacent blade cross sections taken near the outer tips of the buckets and looking radially inward.
SUMMARY OF THE INVENTION Briefly stated, the invention is practiced by arranging adjacent blades so that the blade sections near the outer periphery overlap about A of the total chord length and shaping the blade profiles a convergent-divergent nozzle over the overlapped one-quarter. Each blade profile is characterized by two locations of increased blade thickness, one near the nose and one near the tail section. Over the midsection of the blade profile, the pressure side and suction side are substantially fiat and diverge from one another toward the tail section.
3,565,548 Patented Feb. 23, 1971 DESCRIPTION OF THE PREFERRED EMBODIMENT Referring now to the drawing, there is shown a cross section of two adjacent buckets, designated 1 and 2, taken near the bucket outer tips. It will be understood by those skilled in the art that the configuration and orientation near the radially inner ends of these same buckets will be quite different in appearance and that there is a gradual transition toward the profiles indicated in the drawing. Each bucket profile, such as 2, is divided for the purpose of definition herein into a nose section 3 extending about A of the chord length, a mid-section 4 extending about /2 of the chord length, and a tail section 5 extending the remaining of the chord length. The nose section 3 of one blade overlaps and is roughly coextensive with the tail section 5 of an adjacent bucket.
In the drawing, the blades travel in the direction indicated by the arrow. The upper side 6 is the pressure side of the blades while the lower side 7 is the suction side.
In the nose section 3, the point of greatest blade thick ness is indicated at a and is located back from the leading edge 8 by distance I. The contour of the blade profile on both pressure and suction side over the distance I is quasielliptical and has an l/d ratio satisfying the condition:
From the point of greatest thickness d, the blade narrows toward a neck 11 at the start of the mid-section 4 of the blade. The suction side in this narrowing cross section is gently concave as indicated at 12.
Over the mid-section 4 of the blade, the pressure side and suction side are substantially fiat. It is to be particularly noted also that the flat pressure and suction sides diverge from the relatively narrow neck 11 at the beginning of mid-section 4 to a relatively thick throat portion indicated at its thickest point as t. Throat portion t is located approximately /4 of the chord length along the blade and is so designated because it lies opposite the thickest nose section d to form therewith the throat of a. convergent-divergent nozzle between blades 1, 2.
In some cases, the nose thickness d will be slightly greater than t and in other cases the throat thickness 1 will be slightly greater than a. In either event, however, the two are approximately the same, relative to other parts of the blade.
The tail section 5 of the blade profile comprises a relatively flat suction side which is a continuation of the aforementioned flat suction side over the mid-section of the blade. On the pressure side, the blade curvature is reversed after passing through the throat portion t and caused to curve gently toward the trailing edge 9 to provide a slightly concave surface on the pressure side. The radius of curvature over this portion, designated 10, should be at least 20 times that of the radius of curvature at the throat section I.
OPERATION The operation of the invention is as follows. At the location of the blade profiles 1 and 2 near the outer blade portions, the thickest nose portion d of blade 2 is disposed opposite the thickest throat portion 1 of blade 1 and the two together form a convergent-divergent nozzle of transonic flow conditions indicated at I between the dashed lines. Adjacent zone I is a zone II of supersonic flow and zone III of supersonic flow at essentially constant velocity. The radius of curvature of the concave suction side 12 of blade and the radius of curvature of the concave pressure side 10 of blade 1 are both calculated, preferably using the method of characteristics, which is well know to those skilled in the art, to provide optimum flow conditions.
One advantage of the foregoing design, in having a nose section and a tail section which are substantially the same thickness, is to provide a more symmetrical bucket of greater strength and to allow enough material for shielding against erosion on leading edge at the outer tips. Also, by employing flat profiles over approximately half of the pressure side and approximately 4 of the suction side, simplifications as to blade shaping are introduced.
Well controlled transition from a transonic flow to a supersonic flow in a compressed region between overlapped buckets, such that the static pressures along suction and pressure side of section 5 are converging gradually to the downstream static pressure, adds greatly to the overall efficiency of the transonic bucket described in relation to previously known designs.
While there is shown what is considered at present to be the preferred embodiment of the invention, it is of course understood that various other modifications may be made therein, and it is intended to cover in the appended claims all such modifications as fall within the true spirit and scope of the invention.
What We claim as new and desire to secure by Letters Patent of the United States is:
1. In an axial flow turbine having buckets with tips thereon traveling with respect to elastic fluid passing therethrough under transonic conditions, each of said bucket outer portions being shaped to define a blade profile having a rounded nose section, a mid-section and a tail section extending over approximately the first quarter, the middle half and the last quarter of the chord length respectively,
said nose section increasing and then decreasing in thickness to provide a first reference point of maximum thickness therein,
said mid-section having substantially fiat sides increasing in thickness throughout its length to provide a second reference point of maximum thickness between the mid-section and tail section,
said first and second reference points being of approximately the same blade thickness.
2. In an axial flow turbine having buckets with tips thereon traveling with respect to elastic fluid passing therethrough under transonic and supersonic flow conditions, each of said bucket outer portions being shaped to define a blade profile having a rounded nose section extending over approximately one-quarter of the chord length, a mid-section extending over approximately onehalf of the chord length, and a tail section extending the remaining one-quarter of the chord length,
said nose section disposed in overlapping and coextensive relationship with the tail section of an adjacent blade profile,
said nose section gradually increasing in thickness commencing at the leading edge thereof and then decreasing in thickness,
said mid-section defining substantially flat surfaces on the pressure and suction sides of the profile and also diverging slightly toward the tail section,
said tail section having a substantially fiat suction side which is a continuation of said mid-section suction side and having a surface on the pressure side which gently converges from a maximum throat thickness to the bucket trailing edge.
3. The combination according to claim 2, wherein the contour of the nose section from the leading edge to the thickest nose portion is quasi-elliptical and substantially symmetrical on the pressure and suction sides.
4. The combination according to claim 2, where the maximum thickness of the blade in the nose section and the maximum thickness of the blade at the commencement of the tail section are substantially the same.
5. The combination according to claim 2, wherein the surface of the suction side of the nose section of one blade and the surface of the pressure side of the tail section of an adjacent blade are disposed opposite one another and are slightly concave and shaped to obtain a confined supersonic flow region between blades.
References Cited
US793831*A 1969-01-24 1969-01-24 Transonic buckets for axial flow turbines Expired - Lifetime US3565548A (en)

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FR (1) FR2029035A1 (en)
GB (1) GB1270156A (en)
SE (1) SE358438B (en)

Cited By (22)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3697193A (en) * 1970-12-10 1972-10-10 Adrian Phillips Fluidfoil section
JPS51145008A (en) * 1975-05-31 1976-12-13 Maschf Augsburg Nuernberg Ag Highhperipheral speed impellers for axiallflow thermooturboomachines
US4240952A (en) * 1979-01-15 1980-12-23 Clarence E. Hulbert, Jr. Method of making concrete from fly ash
US4333088A (en) * 1980-11-03 1982-06-01 Exxon Research & Engineering Co. Disposable peristaltic pump assembly for facsimile printer
US4616975A (en) * 1984-07-30 1986-10-14 General Electric Company Diaphragm for a steam turbine
US4643645A (en) * 1984-07-30 1987-02-17 General Electric Company Stage for a steam turbine
US4900230A (en) * 1989-04-27 1990-02-13 Westinghouse Electric Corp. Low pressure end blade for a low pressure steam turbine
US5197854A (en) * 1991-09-05 1993-03-30 Industrial Design Laboratories, Inc. Axial flow fan
US5588804A (en) * 1994-11-18 1996-12-31 Itt Automotive Electrical Systems, Inc. High-lift airfoil with bulbous leading edge
DE19614420A1 (en) * 1996-04-12 1997-10-16 Aloys Wobben Rotor blade for wind power plant
US6068454A (en) * 1998-04-06 2000-05-30 Ford Motor Company Fuel pump with helical impeller
EP1152122A2 (en) * 2000-05-01 2001-11-07 United Technologies Corporation Turbomachinery blade
US20050207893A1 (en) * 2004-03-21 2005-09-22 Chandraker A L Aerodynamically wide range applicable cylindrical blade profiles
US20050220625A1 (en) * 2004-03-31 2005-10-06 Chandraker A L Transonic blade profiles
CN102042040A (en) * 2009-10-23 2011-05-04 通用电气公司 Turbine airfoil
EP2896788A1 (en) * 2014-01-16 2015-07-22 MTU Aero Engines GmbH Extruded profile for producing a guide blade for an exhaust stage
EP2540967A3 (en) * 2011-06-29 2017-06-21 Mitsubishi Hitachi Power Systems, Ltd. Supersonic turbine moving blade and axial-flow turbine
EP2634087A3 (en) * 2012-02-29 2017-08-30 General Electric Company Airfoils for use in rotary machines
US10358926B2 (en) 2017-08-11 2019-07-23 General Electric Company Low-noise airfoil for an open rotor
EP3489462A3 (en) * 2017-11-24 2019-07-24 Rolls-Royce plc Gas turbine engine
EP3489461A3 (en) * 2017-11-24 2019-08-07 Rolls-Royce plc Gas turbine engine
EP4332346A3 (en) * 2022-08-09 2024-06-19 RTX Corporation Fan blade or vane with improved bird impact capability

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FR2728618B1 (en) * 1994-12-27 1997-03-14 Europ Propulsion SUPERSONIC DISTRIBUTOR OF TURBOMACHINE INPUT STAGE
GB201003084D0 (en) 2010-02-24 2010-04-14 Rolls Royce Plc An aerofoil
JP6110544B2 (en) * 2011-06-29 2017-04-05 三菱日立パワーシステムズ株式会社 Supersonic turbine blade and axial turbine
JP6081398B2 (en) * 2014-03-12 2017-02-15 株式会社東芝 Turbine blade cascade, turbine stage and steam turbine

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* Cited by examiner, † Cited by third party
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NL59663C (en) * 1941-08-29
US2935246A (en) * 1949-06-02 1960-05-03 Onera (Off Nat Aerospatiale) Shock wave compressors, especially for use in connection with continuous flow engines for aircraft
CH427851A (en) * 1965-04-01 1967-01-15 Bbc Brown Boveri & Cie Blade ring for transonic flow
FR1473721A (en) * 1965-04-01 1967-03-17 Brown Movable fins for transonic flow
US3333817A (en) * 1965-04-01 1967-08-01 Bbc Brown Boveri & Cie Blading structure for axial flow turbo-machines

Cited By (34)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3697193A (en) * 1970-12-10 1972-10-10 Adrian Phillips Fluidfoil section
JPS51145008A (en) * 1975-05-31 1976-12-13 Maschf Augsburg Nuernberg Ag Highhperipheral speed impellers for axiallflow thermooturboomachines
JPS561443B2 (en) * 1975-05-31 1981-01-13
US4240952A (en) * 1979-01-15 1980-12-23 Clarence E. Hulbert, Jr. Method of making concrete from fly ash
US4333088A (en) * 1980-11-03 1982-06-01 Exxon Research & Engineering Co. Disposable peristaltic pump assembly for facsimile printer
US4616975A (en) * 1984-07-30 1986-10-14 General Electric Company Diaphragm for a steam turbine
US4643645A (en) * 1984-07-30 1987-02-17 General Electric Company Stage for a steam turbine
US4900230A (en) * 1989-04-27 1990-02-13 Westinghouse Electric Corp. Low pressure end blade for a low pressure steam turbine
US5197854A (en) * 1991-09-05 1993-03-30 Industrial Design Laboratories, Inc. Axial flow fan
US5588804A (en) * 1994-11-18 1996-12-31 Itt Automotive Electrical Systems, Inc. High-lift airfoil with bulbous leading edge
DE19614420A1 (en) * 1996-04-12 1997-10-16 Aloys Wobben Rotor blade for wind power plant
DE19614420C2 (en) * 1996-04-12 2003-05-22 Aloys Wobben Rotor blade and wind turbine with a rotor blade
US6068454A (en) * 1998-04-06 2000-05-30 Ford Motor Company Fuel pump with helical impeller
EP1152122A2 (en) * 2000-05-01 2001-11-07 United Technologies Corporation Turbomachinery blade
EP1152122A3 (en) * 2000-05-01 2003-09-17 United Technologies Corporation Turbomachinery blade
US20050207893A1 (en) * 2004-03-21 2005-09-22 Chandraker A L Aerodynamically wide range applicable cylindrical blade profiles
US7179058B2 (en) * 2004-03-21 2007-02-20 Bharat Heavy Electricals Limited Aerodynamically wide range applicable cylindrical blade profiles
US20050220625A1 (en) * 2004-03-31 2005-10-06 Chandraker A L Transonic blade profiles
US7175393B2 (en) * 2004-03-31 2007-02-13 Bharat Heavy Electricals Limited Transonic blade profiles
CN102042040B (en) * 2009-10-23 2016-01-20 通用电气公司 Turbine airfoil
CN102042040A (en) * 2009-10-23 2011-05-04 通用电气公司 Turbine airfoil
EP3828387A1 (en) 2011-06-29 2021-06-02 Mitsubishi Power, Ltd. Turbine moving blade and axial-flow turbine
EP2540967A3 (en) * 2011-06-29 2017-06-21 Mitsubishi Hitachi Power Systems, Ltd. Supersonic turbine moving blade and axial-flow turbine
EP3832068A1 (en) 2011-06-29 2021-06-09 Mitsubishi Power, Ltd. Turbine moving blade and axial-flow turbine
EP2634087A3 (en) * 2012-02-29 2017-08-30 General Electric Company Airfoils for use in rotary machines
US9920640B2 (en) 2014-01-16 2018-03-20 MTU Aero Engines AG Extruded profile for manufacturing a blade of an outlet guide vane
EP2896788A1 (en) * 2014-01-16 2015-07-22 MTU Aero Engines GmbH Extruded profile for producing a guide blade for an exhaust stage
US10358926B2 (en) 2017-08-11 2019-07-23 General Electric Company Low-noise airfoil for an open rotor
EP3489462A3 (en) * 2017-11-24 2019-07-24 Rolls-Royce plc Gas turbine engine
EP3489461A3 (en) * 2017-11-24 2019-08-07 Rolls-Royce plc Gas turbine engine
US10876412B2 (en) 2017-11-24 2020-12-29 Rolls-Royce Plc Gas turbine engine
US10954798B2 (en) 2017-11-24 2021-03-23 Rolls Royce Plc Gas turbine engine with optimized fan blade geometry
US11346229B2 (en) 2017-11-24 2022-05-31 Rolls-Royce Plc Gas turbine engine with optimized fan blade geometry
EP4332346A3 (en) * 2022-08-09 2024-06-19 RTX Corporation Fan blade or vane with improved bird impact capability

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DE2002348B2 (en) 1979-06-13
DE2002348A1 (en) 1970-07-30
CH515412A (en) 1971-11-15
GB1270156A (en) 1972-04-12
FR2029035A1 (en) 1970-10-16
JPS5612681B1 (en) 1981-03-24
SE358438B (en) 1973-07-30
DE2002348C3 (en) 1984-09-06

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