US2429215A - Turbine blade - Google Patents

Turbine blade Download PDF

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Publication number
US2429215A
US2429215A US509801A US50980143A US2429215A US 2429215 A US2429215 A US 2429215A US 509801 A US509801 A US 509801A US 50980143 A US50980143 A US 50980143A US 2429215 A US2429215 A US 2429215A
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US
United States
Prior art keywords
blade
projections
load transmitting
central plane
root
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.)
Expired - Lifetime
Application number
US509801A
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English (en)
Inventor
Boestad Gustav Karl William
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.)
JARVIS C MARBLE
Original Assignee
JARVIS C MARBLE
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 JARVIS C MARBLE filed Critical JARVIS C MARBLE
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Publication of US2429215A publication Critical patent/US2429215A/en
Anticipated expiration legal-status Critical
Expired - Lifetime 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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type

Definitions

  • This invention relates to turbine blades the root of which is provided with two or more projections laterally of the central plane thereof, having load transmitting surfaces engaging and transmitting to the element in which the blade is secured the load due to centrifugal force on the blade.
  • These load transmitting surfaces on each side of the central plane of the rotor are adapted together to transfer the centrifugal force acting upon the turbine blade onto said element, and the intention is to reduce the tensile strains in the blade root and the surface pressures in the load transmitting surfaces, without it being necessary to increase the dimensions of the rotor at right angles to the longitudinal direction of the blade.
  • the known turbine blade attachment appears from Fig. l in the accompanying drawing, which is a partial section at right angles to the axis of rotation of a turbine blade ring.
  • the figure shows a portion I of a turbine blade with blade root I2 and a portion I4 of a rotor.
  • the blade root I2 is recessed at I6, I8 to form two projections, shoulders or the like 20, 22 on both sides of the central plane 24 of the blade root.
  • I8 are projections or the like .26, 28 extending from the rotor I4, against which the projections 20, 22 bear with load transmitting surfaces 30, 32.
  • these load transmitting surfaces are at least approximately parallel to each other on both sides of the centre line 24 of the blade root.
  • the blade when the turbine is brought to a stop (particularly in gas turbines when the fuel supply is cut off), the blade will be cooled down much more rapidly than the rotor, whereby the blade root portion between the surfaces 30 and' 32 is stretched, or the rotor projections will be com pressed, so that there will be a gap in the cold state at the surface 32. In this manner, the root portion will soon be altered toa detrimental extent or destroyed after repeated startings and stoppings of the turbine.
  • these diilic'ulties are eliminated substantially by the fact that the load transmitting surfaces provided on one and the same side of the central plane of the blade root are at an angle with one another.
  • planes extending through the supporting surfaces intersect the central plane of the blade root in lins the distance between which in said plane is essentially less than the average distance between the load transmitting surfaces on one andy the same side of the central plane.
  • FIG. 1 shows portions of a blade and a rotor according to two embodiments of the invention.
  • the figures are illustrated in the same way as in Fig. 1 and moreover the same designations are used for corresponding parts in the figures.
  • the load transmitting surfaces 34 between the projections or the like 20, 26 on the blade root I2 and the rotor i4, respectively, extend at least substantially normally, that is to say, at right angles to the centre line 24 of the blade.
  • the load transmitting surfaces 36 between the inner projections or the like 22, 28 form an angle with the load transmitting surfaces 34 on both sides of the central plane 24 of the blade root. Planes extending through the surfaces 34, 36 meet the central plane 24 in lines coinciding with (see point 3l in Fig. 2) or situated near one another, that is to say so that the spacing of these lines is less than the average spacing of the load transmitting surfaces.
  • the load transmitting surface 3l also forms an angle with the blade axis, but in the opposite direction to the load transmitting surface 36.
  • Planes extending through the load transmitting surfaces 34, 36 on the same side of the centre line 24 may intersect each other in a point 38 according to Fig. 3, which is situated on the opposite side'of the centre line 24.
  • the construction according to Fig. 3 has the advantage that the angle of inclination of the load transmitting surface 3B may be made less steep.
  • the blades may be made from austenitic steel, while the rotor, which is adapted to be cooled, if desired, is made from martensitic steel, as will appear more fully from the co-pending patent application No. 509,800 of G. K. W. Boestad et al., filed November 10, 1943, to which reference is made for a more detailed description.
  • Ihe invention is primarily intended to be used in rotational blades, but in certain cases it may also be applied to guide blades.
  • the projections, bosses or teeth of the blade root may be placed non-'symmetrically laterally of the central plane of the rotor, and may be displaced relatively to each other in the longitudinal direction of the blade.
  • a blade having a root portion with a plurality of laterally extending projections on the same side of the central plane of the blade providing radially spaced load transmitting surfaces engaging and transmitting to said element the load due to centrifugal force on the blade, said surfaces ⁇ being at different angles relative tovsaid central plane and clearance being provided between-said element and other surfaces of said projections to permit expansion and contraction of the projections.
  • a blade having a root portion with a plurality of laterally extending projections on the surfaces being located so that the projected planes thereof converge in the direction toward said central plane and clearance being provided between said element and other surfaces of said projections to permit expansion and contraction of the projections.
  • a blade having a root portion with a plurality of laterally extending projections on the same side of the central plane of the blade providing radially spaced load transmitting surfaces engaging and transmitting to said element the load due to centrifugal force on the blade, said surfaces being located so that the projected planes thereof converge to intersect at a place substantially coincident with saidcentral plane and clearance being provided between said element and other surfaces of said projections to permit expansion and contraction of the projections.
  • a blade having a root portion with a plurality of laterally extending projections on the same side of the central plane of the blade providing radially spaced load transmitting surfaces engaging and transmitting to said element the loady due to centrifugal force on the blade, said surfaces being located so that the projected planes thereof converge to intersect at a place on the side of said central plane opposite the side thereof on which said surfaces are located and clearance being provided between said element and other surfaces of said projections to permit expansion and contraction of the projections.
  • a blade having a root portion with a plurality of laterally .extending projections on the same side of the central plane of the blade providing radially spaced load transmitting surfaces engaging and transmitting to said element the load due to centrifugal force on the blade, the radially innermost and the radially outermost of said surfaces being located obliquely with respect to said central plane, the projected planes of said surfaces converging to intersect at a place located radially intermediate said surfaces and clearance being provided between said element and other surfaces of said projections to permit expansion and contraction of the projections.
  • a blade having a root portion with a plurality of laterally extending projections on the same side of the central plane of the blade providing radially spaced load transmitting surfaces engaging and transmitting to said element the load due to centrifugal force on the blade, the radially outermost of said surfaces being substantially normal to said central plane, the radially innermost of said surfaces being located obliquely relative to said plane and sloping radially outwardly in the direction toward said plane and clearance being provided between said element and other surfaces of said projections to permit expansion and contraction of the projections.
  • a turbine having a blade carrying element, a blade having a root portion with a plurality of laterally extending projections on the same side of the central plane of the blade providing radially spaced load transmitting surfaces engaging and transmitting to said element the load due to centrifugal force on the blade,

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US509801A 1943-01-16 1943-11-10 Turbine blade Expired - Lifetime US2429215A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
SE249717X 1943-01-16

Publications (1)

Publication Number Publication Date
US2429215A true US2429215A (en) 1947-10-21

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ID=20306139

Family Applications (1)

Application Number Title Priority Date Filing Date
US509801A Expired - Lifetime US2429215A (en) 1943-01-16 1943-11-10 Turbine blade

Country Status (4)

Country Link
US (1) US2429215A (de)
CH (1) CH249717A (de)
FR (1) FR901235A (de)
GB (1) GB574759A (de)

Cited By (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2683018A (en) * 1948-10-01 1954-07-06 Maschf Augsburg Nuernberg Ag Turbine rotor with ceramic blades
US3922109A (en) * 1972-08-29 1975-11-25 Mtu Muenchen Gmbh Rotor for flow machines
US4191509A (en) * 1977-12-27 1980-03-04 United Technologies Corporation Rotor blade attachment
US4813850A (en) * 1988-04-06 1989-03-21 Westinghouse Electric Corp. Integral side entry control stage blade group
US4820126A (en) * 1988-02-22 1989-04-11 Westinghouse Electric Corp. Turbomachine rotor assembly having reduced stress concentrations
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine
US20060197400A1 (en) * 2005-03-03 2006-09-07 Andrea De Simone Rotating machine
US20080050238A1 (en) * 2006-08-24 2008-02-28 Pratt & Whitney Canada Corp. Disc firtree slot with truncation for blade attachment
US20090208339A1 (en) * 2008-02-15 2009-08-20 United Technologies Corporation Blade root stress relief
FR2937370A1 (fr) * 2008-10-16 2010-04-23 Snecma Disque de roue de turbine.
EP2762676A1 (de) * 2013-02-04 2014-08-06 Siemens Aktiengesellschaft Turbomaschinen-Rotorschaufel, Turbomaschinen-Rotorscheibe, Turbomaschinenrotor und Gasturbinenmotor mit unterschiedlichen Kontaktflächenwinkeln des Schaufelfusses und der Schaufelnut
US10895160B1 (en) * 2017-04-07 2021-01-19 Glenn B. Sinclair Stress relief via unblended edge radii in blade attachments in gas turbines

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5183389A (en) * 1992-01-30 1993-02-02 General Electric Company Anti-rock blade tang
EP2392589A3 (de) 2005-11-11 2012-06-20 Vertex Pharmaceuticals Incorporated Hepatitis-C-Virusvarianten

Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB279312A (en) * 1927-03-10 1927-10-27 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
US2058479A (en) * 1933-03-10 1936-10-27 Milo Ab Turbine for hot driving media
US2153681A (en) * 1936-05-28 1939-04-11 Elastic Stop Nut Corp Fastening means and method of manufacture thereof
US2220616A (en) * 1936-02-29 1940-11-05 Roder Karl Packing for steam turbines
CH217031A (de) * 1940-11-23 1941-09-30 Boehmisch Maehrische Maschinen Laufscheibe mit im Stillstand verstellbaren Laufschaufeln für axial durchströmte Rotationsmaschinen.
GB546515A (en) * 1940-03-26 1942-07-16 Bbc Brown Boveri & Cie Improvements in or relating to intermediate pieces for the blading of steam or gas turbines
US2295012A (en) * 1941-03-08 1942-09-08 Westinghouse Electric & Mfg Co Turbine blading

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB279312A (en) * 1927-03-10 1927-10-27 British Thomson Houston Co Ltd Improvements in and relating to elastic fluid turbines
US2058479A (en) * 1933-03-10 1936-10-27 Milo Ab Turbine for hot driving media
US2220616A (en) * 1936-02-29 1940-11-05 Roder Karl Packing for steam turbines
US2153681A (en) * 1936-05-28 1939-04-11 Elastic Stop Nut Corp Fastening means and method of manufacture thereof
GB546515A (en) * 1940-03-26 1942-07-16 Bbc Brown Boveri & Cie Improvements in or relating to intermediate pieces for the blading of steam or gas turbines
CH217031A (de) * 1940-11-23 1941-09-30 Boehmisch Maehrische Maschinen Laufscheibe mit im Stillstand verstellbaren Laufschaufeln für axial durchströmte Rotationsmaschinen.
US2295012A (en) * 1941-03-08 1942-09-08 Westinghouse Electric & Mfg Co Turbine blading

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2683018A (en) * 1948-10-01 1954-07-06 Maschf Augsburg Nuernberg Ag Turbine rotor with ceramic blades
US3922109A (en) * 1972-08-29 1975-11-25 Mtu Muenchen Gmbh Rotor for flow machines
US4191509A (en) * 1977-12-27 1980-03-04 United Technologies Corporation Rotor blade attachment
US4820126A (en) * 1988-02-22 1989-04-11 Westinghouse Electric Corp. Turbomachine rotor assembly having reduced stress concentrations
US4813850A (en) * 1988-04-06 1989-03-21 Westinghouse Electric Corp. Integral side entry control stage blade group
US5001830A (en) * 1989-10-23 1991-03-26 Westinghouse Electric Corp. Method for assembling side entry control stage blades in a steam turbine
US7628581B2 (en) * 2005-03-03 2009-12-08 Alstom Technology Ltd. Rotating machine
US20060197400A1 (en) * 2005-03-03 2006-09-07 Andrea De Simone Rotating machine
US20080050238A1 (en) * 2006-08-24 2008-02-28 Pratt & Whitney Canada Corp. Disc firtree slot with truncation for blade attachment
US20090208339A1 (en) * 2008-02-15 2009-08-20 United Technologies Corporation Blade root stress relief
FR2937370A1 (fr) * 2008-10-16 2010-04-23 Snecma Disque de roue de turbine.
EP2762676A1 (de) * 2013-02-04 2014-08-06 Siemens Aktiengesellschaft Turbomaschinen-Rotorschaufel, Turbomaschinen-Rotorscheibe, Turbomaschinenrotor und Gasturbinenmotor mit unterschiedlichen Kontaktflächenwinkeln des Schaufelfusses und der Schaufelnut
US20150361803A1 (en) * 2013-02-04 2015-12-17 Siemens Aktiengesellschaft Turbomachine rotor blade, turbomachine rotor disc, turbomachine rotor, and gas turbine engine with different root and slot contact face angles
JP2016507024A (ja) * 2013-02-04 2016-03-07 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ ターボ機械ロータブレード、ターボ機械ロータディスク、ターボ機械ロータ、複数のルートおよびスロット接触面角を有するガスタービンエンジン
RU2633287C2 (ru) * 2013-02-04 2017-10-11 Сименс Акциенгезелльшафт Лопасть ротора турбомашины, диск ротора турбомашины, ротор турбомашины и газотурбинный двигатель с разными углами контактной поверхности хвостовика и гнезда
US9903213B2 (en) * 2013-02-04 2018-02-27 Siemens Aktiengesellschaft Turbomachine rotor blade, turbomachine rotor disc, turbomachine rotor, and gas turbine engine with different root and slot contact face angles
US10895160B1 (en) * 2017-04-07 2021-01-19 Glenn B. Sinclair Stress relief via unblended edge radii in blade attachments in gas turbines

Also Published As

Publication number Publication date
FR901235A (fr) 1945-07-20
CH249717A (de) 1947-07-15
GB574759A (en) 1946-01-18

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