US3603143A - Apparatus for testing the vane anchorage of turbine vanes - Google Patents

Apparatus for testing the vane anchorage of turbine vanes Download PDF

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Publication number
US3603143A
US3603143A US827537A US3603143DA US3603143A US 3603143 A US3603143 A US 3603143A US 827537 A US827537 A US 827537A US 3603143D A US3603143D A US 3603143DA US 3603143 A US3603143 A US 3603143A
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United States
Prior art keywords
vane
rotor
force
turbine
yoke
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Expired - Lifetime
Application number
US827537A
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English (en)
Inventor
Klaus Detert
Hans-Jochen Lipp
Erich Winschuh
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Licentia Patent Verwaltungs GmbH
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Licentia Patent Verwaltungs GmbH
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
    • G01M13/00—Testing of machine parts
    • 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

Definitions

  • the apparatus operates by applying forces to a vane, which includes a vane base, attached in the normal fashion to a simulated portion of a turbine rotor.
  • a force in a direction corresponding to the radial direction in a turbine rotor and hence to the direction of centrifugal force in a rotating rotor is applied by attaching the vane and rotor portion to respective first and second yokes separated by resilient elements and drawing the vane and rotor portions apart.
  • a force in a direction corresponding to the axial and/or tangential directions of a turbine rotor and hence the direction of the forces of the driving fluid which act on the vanes during operation of a turbine is applied by an additional device while the vane and rotor portions are held in the yokes.
  • the present invention relates to a testing device for determining tightness, deformations (warping) and weak points of the vane anchorage of turbine vanes.
  • An object of the present invention is to provide suitable apparatus which simulates the centrifugal and fluid (.e.g., steam) forces which act, in practice, upon the vane anchorage of turbine vanes. More particularly, it is an object of the present invention to provide a device which permits the determination of the elastic deformation s in the base of a turbine vane; detection of any tilting or slippage of a turbine vane; as well as the location of the weak points of a turbine vane at which possible permanent deformations, cracks or breaks may occur through an overstress during operation of a turbine.
  • the simulated rotor portion is attached to a first yoke, the vane is attached to a second yoke and the two yokes are supported in a spaced-apart relationship by means of suitable resilient elements.
  • the means for applying the force corresponding to the centrifugal force is realized by a device for attaching the second yoke to the simulated rotor portion.
  • the means which apply the force to the vane to simulate the force of a driving fluid include means for periodically varying this force.
  • means are provided to heat the joint between the simulated rotor portion and the vane.
  • the motion-detecting device is realized by a light-optical measuring instrument while the deformations can be measured by devices such as dial gauges.
  • FIG. I is a cross-sectional view through a portion of the testing apparatus according to a preferred embodiment of the present invention.
  • FIG. 2 is an elevational, and partly schematic illustration of apparatus for simulating the application of the forces of a driving fluid in the testing apparatus of FIG. 1.
  • FIG. 3 is an enlarged cross-sectional view of a portion of the apparatus of FIG. 1 showing a joint comprising the straddling base ofa turbine vane and an impeller hub ofa turbine rotor.
  • FIG. 4 is a schematic illustration of a light-optical measuring device which may be used in the apparatus of FIG. 1.
  • the testing apparatus illustrated in FIG. 1 comprises an adjustable frame 1 constructed to hold a turbine vane 2 together with a rotor segment 3 and a shaft or shank 4.
  • the frame 1 includes two yokes 5 and 8 which are mounted on support columns 9 and 10.
  • the turbine vane 2 is fastened in the central portion of the frame 1 on the yoke 5 which has a U- shaped profile.
  • the yokes 5 and 8 are spaced apart by braces 6 and 7 consisting of resilient elements 11 and 13 and supporting sleeves l2 and 14, respectively.
  • a hydraulic stretching or pulling device 15 is arranged on the yoke 8 and provided with a pull rod 16 which has one end attached to the shaft 4 of the rotor segment 3.
  • the shaft 4 is guided in a sleeve 17 fastened to the yoke 8.
  • the shaft 4 is therefore supported by the pulling device 15, which, in turn, abuts against the yoke 8.
  • the top plate 18 of the vane 2 is welded to a plate 19 that is bolted to the yoke 5.
  • the yoke 5 is braced with respect to the yoke 8 by the resilient elements 11 and 13.
  • These resilient elements may, for example, consist of laminations of metal and rubber.
  • the purpose of the resilient elements is to allow the yoke 5, and thus the vane 2, sufficient freedom of movement in the horizontal direction; that is, in the direction corresponding to the tangential and/or axial direction of the assumed rotor.
  • the pulling device 15 which is supplied with a hydraulic fluid under pressure, operates to apply a static force to the turbine vane anchor: i.e., a force which corresponds to the centrifugal force acting on a rotating rotor.
  • the magnitude of this force can be adjusted and measured by controlling and measuring the hydraulic pressure.
  • this vertically acting force can be measured by means of the spring deflection of the resilient elements 11 and 13.
  • the joint between the vane 2 and the rotor segment 3 is preferably heated, by a heating device 50, to the temperatures reached during operation.
  • FIG. 2 schematically illustrates a preferred embodiment of apparatus, according to the present invention, for applying forces to the vane 2 which correspond to the forces of a vanedriving fluid; that is, for example, the forces applied to the vanes of a turbine by steam.
  • This force-applying apparatus includes a loop 30 of wire rope arranged to surround the vane blade, a length of wire rope 31, a tension-controlling device 32 and a spring 33. By tensioning the wire rope 31 with the device 32 a prescribed force can be applied to the turbine blade 2 in the horizontal direction.
  • the force can be exerted in a direction corresponding to the axial and/or tangential directions as defined by the assumed rotor.
  • a force in the axial direction effects a bending in the maximum direction" and possibly causes the blade to tilt.
  • a force applied in the tangential direction effects a bending in the minimum direction" and possibly causes the vane 2 to slide on the rotor segment 3.
  • wire rope 34 can therefore be moved back and forth at a frequency, for example, of 3 Hz. Since the forces of a driving fluid such as steam result in impulses on turbine vanes in the axial direction, first in the direction of the emerging steam and then in the opposite direction, the vane 2 can also be tensioned in the identical manner in the opposite direction by the wire rope 31.
  • the movement of the base of the vane with respect to the rotor segment 3 during the application, to the vane 2, of the horizontal loading forces is measured by viewing the change in the angular position between two suitable external surfaces on the rotor segment and the base of the vane.
  • This angular change is determined by a light-optical device which employs mirrors 40 and 41 arranged on the external surfaces of the elements 2 and 3 as shown in FIG. 3.
  • FIG. 4 schematically illustrates the construction of this lightoptical measuring device.
  • the device is provided with a light source 42 and a measuring'screen 43 having a suitable scale.
  • the mirrors 40 and 41 reflect a light beam from the light source 42 to the screen 43.
  • the forces acting on the vane2 produce small movements within the vane anchorage which result in a displacement of the light marks on the screen 43.
  • a properly rigid coupling between the base of the vane and the rotor seginent leads to identical movements in the reflected light beams.
  • a relative motion between the vane base and the rotor segment results in a change in the distance between the light marks on the screen. If the relative movements remain within the elastic limits of the vane and rotor, this change will be small. However, if the vane 2 tilts or slides with respect to the rotor segment 3, there will be a considerable change in the distance between the marks.
  • Measuring elements such as dial gauges 51 can also be applied at the points 24 in the middle of the vane 2 to measure the spread at the base of the vane in relation to the applied force Z. This measurement makes it possible to determine when one or both of the sides of the vane base come in contact with the retaining catches of the rotor segment 3. By removal of the retaining catches it is also possible to determine the spread at the base of the vane for all vaiues of applied force.
  • the principal component of the forces applied by the driving fluid acts in the circumferential direction of the assumed rotor. By tensioning the wire rope in this direction, it is possible, with the apparatus according to the.
  • the vane-driving fluid also exerts forces, or rather force impulses, on a vane in the axial direction of the assumed rotor.
  • the wire rope By rotating the yanc on its mountb the wire rope can be employed to simulate these axia ly directed forces to investigate their effects.
  • a. means simulating a portion of a turbine rotor
  • vane means comprising at least a portion of a turbine vane and a vane base, attached to said rotor portion;
  • resilient element means for resiliently supporting said first yoke with respect to said second yoke, said first and second yokes and said resilient means forming a frame for supporting said vane means;
  • second means for attaching said second yoke to said simulated rotor portion said second means including means-for applying a force to said simulated rotor portion corresponding to the radial direction of a rotor and hence to the direction of the centrifugal force in a rotating rotor;

Landscapes

  • Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Testing Of Devices, Machine Parts, Or Other Structures Thereof (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Force Measurement Appropriate To Specific Purposes (AREA)
US827537A 1968-05-25 1969-06-26 Apparatus for testing the vane anchorage of turbine vanes Expired - Lifetime US3603143A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE19681773500 DE1773500B2 (de) 1968-05-25 1968-05-25 Pruefeinrichtung zur bestimmung der kraftschluessigkeit und verformung sowie von schwachstellen der schaufelbefestigung von turbinenschaufeln

Publications (1)

Publication Number Publication Date
US3603143A true US3603143A (en) 1971-09-07

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US827537A Expired - Lifetime US3603143A (en) 1968-05-25 1969-06-26 Apparatus for testing the vane anchorage of turbine vanes

Country Status (4)

Country Link
US (1) US3603143A (de)
CH (1) CH480627A (de)
DE (1) DE1773500B2 (de)
GB (1) GB1226894A (de)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3690160A (en) * 1969-04-09 1972-09-12 Licentia Gmbh Apparatus for testing the blade anchorage of turbine blades
US3802255A (en) * 1972-03-08 1974-04-09 Us Air Force Fixture for tensile and stress rupture testing of turbine blades
US6718833B2 (en) 2001-03-05 2004-04-13 Adtech Systems Research, Inc. Multiaxial high cycle fatigue test system
US20100145836A1 (en) * 2005-10-04 2010-06-10 Basepoint Analytics Llc System and method of detecting fraud
EP2241872A2 (de) 2009-04-15 2010-10-20 Rolls-Royce Plc Vorrichtung und Verfahren zur Simulierung der Lebensdauer und/oder der Belastung einer Rotorschaufel und Rotorscheibenbefestigung
CN104792606A (zh) * 2015-02-01 2015-07-22 山东科技大学 锚杆锚固质量检测方法
US20170241860A1 (en) * 2014-09-26 2017-08-24 Vestas Wind Systems A/S Fatigue testing of a wind turbine blade
CN108279122A (zh) * 2018-02-11 2018-07-13 厦门大学嘉庚学院 弹簧铆压可靠性测试装置及使用方法
CN108426783A (zh) * 2017-02-14 2018-08-21 中国石油天然气集团公司 一种微剪切试验装置
CN111398063A (zh) * 2020-03-31 2020-07-10 中国地质大学（武汉） 基于轴力计锚固节理面剪切荷载-剪切位移曲线预测方法

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE3139864C2 (de) * 1981-10-07 1987-04-30 Daimler-Benz Ag, 7000 Stuttgart Verfahren zur Ermittlung der Verformung eines Ventiltriebes an einer Brennkraftmaschine
DE102005016307B4 (de) * 2005-04-09 2010-10-07 Mtu Aero Engines Gmbh Vorrichtung zur Probenprüfung

Citations (7)

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Publication number Priority date Publication date Assignee Title
US1409842A (en) * 1916-01-08 1922-03-14 Tinius Olsen Testing Mach Co Testing machine
US1485835A (en) * 1922-03-09 1924-03-04 Bothezat George De Machine for testing sheet metal for vibration
US2007286A (en) * 1932-05-25 1935-07-09 Schopper Alfred Flexure testing machine
US2469346A (en) * 1945-06-14 1949-05-03 Budd Co Fatigue-testing machine
US2496632A (en) * 1944-12-14 1950-02-07 Baldwin Locomotive Works Vibration testing apparatus
US2917918A (en) * 1956-10-03 1959-12-22 Jules E Jenkins Vibration measuring and recording apparatus
US2984110A (en) * 1955-02-12 1961-05-16 Simek Jiri Optical vibrometer

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1409842A (en) * 1916-01-08 1922-03-14 Tinius Olsen Testing Mach Co Testing machine
US1485835A (en) * 1922-03-09 1924-03-04 Bothezat George De Machine for testing sheet metal for vibration
US2007286A (en) * 1932-05-25 1935-07-09 Schopper Alfred Flexure testing machine
US2496632A (en) * 1944-12-14 1950-02-07 Baldwin Locomotive Works Vibration testing apparatus
US2469346A (en) * 1945-06-14 1949-05-03 Budd Co Fatigue-testing machine
US2984110A (en) * 1955-02-12 1961-05-16 Simek Jiri Optical vibrometer
US2917918A (en) * 1956-10-03 1959-12-22 Jules E Jenkins Vibration measuring and recording apparatus

Non-Patent Citations (2)

* Cited by examiner, † Cited by third party
Title
Fatigue Testing, Weibull 1961 TA 413 W4 pp. 32, 33, 50, 51 *
Kennedy et al., Creep & Fatigue, Journal of Scientific Instruments Vol. 33, Nov. 1956 pp. 409 410. *

Cited By (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3690160A (en) * 1969-04-09 1972-09-12 Licentia Gmbh Apparatus for testing the blade anchorage of turbine blades
US3802255A (en) * 1972-03-08 1974-04-09 Us Air Force Fixture for tensile and stress rupture testing of turbine blades
US6718833B2 (en) 2001-03-05 2004-04-13 Adtech Systems Research, Inc. Multiaxial high cycle fatigue test system
US20100145836A1 (en) * 2005-10-04 2010-06-10 Basepoint Analytics Llc System and method of detecting fraud
EP2241872A2 (de) 2009-04-15 2010-10-20 Rolls-Royce Plc Vorrichtung und Verfahren zur Simulierung der Lebensdauer und/oder der Belastung einer Rotorschaufel und Rotorscheibenbefestigung
EP2241873A2 (de) 2009-04-15 2010-10-20 Rolls-Royce Plc Vorrichtung und Verfahren zur Simulierung der Lebensdauer und/oder der Belastung einer Rotorschaufel und Rotorscheibenbefestigung
US20100263453A1 (en) * 2009-04-15 2010-10-21 Rolls-Royce Plc Apparatus and method for simulating lifetime of and/or stress experienced by a rotor blade and rotor disc fixture
US8505388B2 (en) 2009-04-15 2013-08-13 Rolls-Royce, Plc Apparatus and method for simulating lifetime of and/or stress experienced by a rotor blade and rotor disc fixture
EP3198255B1 (de) * 2014-09-26 2019-01-09 Vestas Wind Systems A/S Ermüdungsprüfung einer windturbinenschaufel
US20170241860A1 (en) * 2014-09-26 2017-08-24 Vestas Wind Systems A/S Fatigue testing of a wind turbine blade
US10209160B2 (en) * 2014-09-26 2019-02-19 Vestas Wind Systems A/S Fatigue testing of a wind turbine blade
CN104792606A (zh) * 2015-02-01 2015-07-22 山东科技大学 锚杆锚固质量检测方法
CN108426783A (zh) * 2017-02-14 2018-08-21 中国石油天然气集团公司 一种微剪切试验装置
CN108426783B (zh) * 2017-02-14 2020-08-07 中国石油天然气集团公司 一种微剪切试验装置
CN108279122A (zh) * 2018-02-11 2018-07-13 厦门大学嘉庚学院 弹簧铆压可靠性测试装置及使用方法
CN108279122B (zh) * 2018-02-11 2023-08-01 厦门大学嘉庚学院 弹簧铆压可靠性测试装置及使用方法
CN111398063A (zh) * 2020-03-31 2020-07-10 中国地质大学（武汉） 基于轴力计锚固节理面剪切荷载-剪切位移曲线预测方法
CN111398063B (zh) * 2020-03-31 2021-04-27 中国地质大学（武汉） 基于轴力计锚固节理面剪切荷载-剪切位移曲线预测方法

Also Published As

Publication number Publication date
DE1773500A1 (de) 1970-11-12
GB1226894A (de) 1971-03-31
DE1773500B2 (de) 1971-11-25
CH480627A (de) 1969-10-31

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