US3185441A - Shroud-blading for turbines or compressors - Google Patents

Shroud-blading for turbines or compressors Download PDF

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Publication number
US3185441A
US3185441A US215617A US21561762A US3185441A US 3185441 A US3185441 A US 3185441A US 215617 A US215617 A US 215617A US 21561762 A US21561762 A US 21561762A US 3185441 A US3185441 A US 3185441A
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United States
Prior art keywords
shroud
blades
blading
shroud plates
plates
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US215617A
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Reuter Hermann
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BBC Brown Boveri AG Switzerland
BBC Brown Boveri France SA
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BBC Brown Boveri France SA
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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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making
    • Y10T29/4932—Turbomachine making
    • Y10T29/49321—Assembling individual fluid flow interacting members, e.g., blades, vanes, buckets, on rotary support member

Definitions

  • the invention relates to shroud-blading for turbines or compressors with which the shroud consists ofseparate shroud plates, the latter not being rigidly connected to one another.
  • the task of the invention is to provide a shroud blading for turbines or compressors with which the shroud consists of separate shroud plates, the latter not being rigidly connected with one another, the said blading guarantees suflicient damping of the blade oscillations while still avoiding the aforementioned disadvantages.
  • the blades are subjected, during the assembly to a torsional stressing, e.g. in an anti-clockwise direction so as to decrease the angle (a) between lines of contact of the edges of the shroud plates of adjacent blades and a line intersecting such contact lines and which extends parallel to the axis of the rotor.
  • the blades and hence also their shroud plates exhibit a continuous inherent tendency to relieve the stress by untwisting, i.e. by turning back in the opposite direction, i.e. in the present case clockwise, and increase the angle a.
  • FIG. 1 is a perspective view, FIG. 2 a side view and FIG. 3 a plan view of the invention.
  • the shroud plates have a parallelogram-shaped base section viewed in the direction of the blade longitudinal axis and form together the shroud for the blading.
  • the mutual lines of contact 4, 5 of the shroud plates 2 include an angle with a straight line running parallel to the machine axis, in the assembled and working condition.
  • the metallic blades 1 are made from conventional blading material which is inherently elastic and hence possess an inherent property of being able to recover from stresses imposed within the elastic limit of the material upon relief of torsional stressing forces to which they are subjected. The recovery is ice only partial since the blades remain under a torsional stressing even after assembly.
  • the torsional stressing is accomplished by flexing in a torsional manner the shank portions of the blades carrying the shroud plates relative to the root portion of the blades which remain fixed, thereby to establish a continuous frictional pressure engagement between the adjoining side faces of the shroud plates brought about by the inherent tendency in the blading to recover its normal unstressed condition.
  • FIG. 3 a plan view of the shroud plates is represented in which view is indicated with 8, a straight line cutting the lines of contact of adjacent shroud plates and running parallel to the turbine or compressor axis and, with a the angle included by this straight line 8 and the lines of contact of the shroud plates.
  • blades are stressing torsionally so as to be twisted on their longitudinal axis-in the case of the constructional example, anticlockwise so as to decrease angle (It-21 gap is then formed temporarily between the shroud plates 2 which at the same time adopt the position indicated in FIG. 1 by dot-dashed line 3.
  • the stressing is released, the restoring force which inherently ensues results in a twisting of the blades in a clockwise direction, which corresponds thus to an increase in angle or, causes on the other hand the separate shroud plates to lie, or resp., press against one another.
  • the blades 1 are so shaped that they display in the assembled static condition, as well as in the working condition with the rotor, for example, operating at normal speed, a torsional stressing which in the case of the constructional example results in a tendency for the blades to twist back in clockwise direction so that the shroud plates of adjacent blades will always be pressed against one another in the circumferential direction.
  • this design Compared with the blade design employing wires to damp the oscillation, this design has an additional advantage in that the oscillations are also damped when all the blades are oscillating in phase or when damping wires would not be sufficiently firmly pressed by the centrifugal or flow forces.
  • the blades can twist against the pre-applied torsional stressing so that angle at diminishes, on thermal expansions appearing, by this means the distance apart of the contact lines 4 and 5 of the individual shroud plates, as projected on to the blading periphery, remains constant. At the same time it is guaranteed by the measurement of angle given above, that this twisting of the blades which compensates the thermal expansions is not reduced as a result of self-restraint by friction.
  • the surfaces of contact 6, 7 of the shroud plates 2 can be treated by any known method, such as by chrome plating, for the reduction of friction or, resp., the easing of the compensating movements.
  • a reduction of this type in the friction does not have a detrimental effect on the damping of the oscillations as by means of the arrangement as according to the invention the blade oscillations are not to be completely checked but correspondingly damped by friction.
  • the invention is not limited solely to the constructional example, it can, for example, be employed both for moving and guide blading.
  • a shrouded bl-ading assembly for rotary machines such as turbines and compressors, each blade being composed of a material having an inherent property of recovery from torsional stressing forces imposed within the elastic limit of the material, each said blade including as an integral part thereof a shroud plate constituting its appertaining portion of the complete shroud ring established by the assembly of all blades, said shroud plates having the configuration of a parallelogram and with adjoining side faces thereof lying in contact with each other at an angle which is oblique to the axis of rotation of said machine, said blades being stressed torsionally from an unstressed condition by torsional flexure of the shank portions thereof carrying said shroud plates relative to the fixed root portions of the blades thereby to establish a continuous frictional pressure engagement between the adjoining side faces of said shroud plates brought about by the inherent tendency in the blading to recover its normal unstressed condition.

Description

May 25, 1965 H. REUTER SHROUD-BLADING FOR TURBINES OR COMPRESSORS Filed Aug. 8, 1962 Fig. 3
INVENTOR. Hermann Rev-her BY fiat/kw, JWM 2.1%!
United States Patent 2 Claims. (51. 253-77 The invention relates to shroud-blading for turbines or compressors with which the shroud consists ofseparate shroud plates, the latter not being rigidly connected to one another.
With the construction of turbines and compressors the designer must strive to form the blades so that their natural frequencies do not coincide with the exciting frequencies. This can not, however, be achieved in all cases.
The attainment of this goal is made more difficult especially when additional unpredictable exciting oscillations can occur so that it can lead to resonance and thus to blade failures. To avoid this means of damping the blade oscillations are provided.
It is, for example, a known procedure to thread wires through drillings in the blades circumferentially with respect to the blading, which wires are pressed against the sides of the drillings due to the effect of the centrifugal or other forces and the oscillations thus damped by friction. Wires of this type cause additional flow losses.
The task of the invention is to provide a shroud blading for turbines or compressors with which the shroud consists of separate shroud plates, the latter not being rigidly connected with one another, the said blading guarantees suflicient damping of the blade oscillations while still avoiding the aforementioned disadvantages. For this purpose the blades are subjected, during the assembly to a torsional stressing, e.g. in an anti-clockwise direction so as to decrease the angle (a) between lines of contact of the edges of the shroud plates of adjacent blades and a line intersecting such contact lines and which extends parallel to the axis of the rotor.
After assembly, the blades and hence also their shroud plates exhibit a continuous inherent tendency to relieve the stress by untwisting, i.e. by turning back in the opposite direction, i.e. in the present case clockwise, and increase the angle a. This forces the lines of contact between the edges of the shroud plates of adjacent blades to press tightly against each other even during normal running speed of the rotor and hence the contact surfaces of adjacent shroud plates rub against one another laterally when oscillations arise, by which means a damping of the oscillations is attained in a simple manner without the employment of additional design measures being neces sary. i l
A constructional example of the invention is described below with the aid of the drawings.
FIG. 1 is a perspective view, FIG. 2 a side view and FIG. 3 a plan view of the invention.
In FIG.1 blades 1, with shroud plates 2 are represented.
The shroud plates have a parallelogram-shaped base section viewed in the direction of the blade longitudinal axis and form together the shroud for the blading.
As is to be seen from FIG. 1, the mutual lines of contact 4, 5 of the shroud plates 2 include an angle with a straight line running parallel to the machine axis, in the assembled and working condition. The metallic blades 1 are made from conventional blading material which is inherently elastic and hence possess an inherent property of being able to recover from stresses imposed within the elastic limit of the material upon relief of torsional stressing forces to which they are subjected. The recovery is ice only partial since the blades remain under a torsional stressing even after assembly. The torsional stressing is accomplished by flexing in a torsional manner the shank portions of the blades carrying the shroud plates relative to the root portion of the blades which remain fixed, thereby to establish a continuous frictional pressure engagement between the adjoining side faces of the shroud plates brought about by the inherent tendency in the blading to recover its normal unstressed condition. In FIG. 3 a plan view of the shroud plates is represented in which view is indicated with 8, a straight line cutting the lines of contact of adjacent shroud plates and running parallel to the turbine or compressor axis and, with a the angle included by this straight line 8 and the lines of contact of the shroud plates. If the blades are stressing torsionally so as to be twisted on their longitudinal axis-in the case of the constructional example, anticlockwise so as to decrease angle (It-21 gap is then formed temporarily between the shroud plates 2 which at the same time adopt the position indicated in FIG. 1 by dot-dashed line 3. When the stressing is released, the restoring force which inherently ensues results in a twisting of the blades in a clockwise direction, which corresponds thus to an increase in angle or, causes on the other hand the separate shroud plates to lie, or resp., press against one another.
The blades 1 are so shaped that they display in the assembled static condition, as well as in the working condition with the rotor, for example, operating at normal speed, a torsional stressing which in the case of the constructional example results in a tendency for the blades to twist back in clockwise direction so that the shroud plates of adjacent blades will always be pressed against one another in the circumferential direction.
Now when bending oscillations occur at the blades as shown in FIG. 2, the shroud plates rub against one another with their surfaces 6 and 7 in direction of arrow 9 so that the oscillations are damped.
Compared with the blade design employing wires to damp the oscillation, this design has an additional advantage in that the oscillations are also damped when all the blades are oscillating in phase or when damping wires would not be sufficiently firmly pressed by the centrifugal or flow forces.
Due to the stressing it is additionally achieved that the basic torsional oscillation at least can not occur.
As there is no play in the assembled and working condition between the shroud plates, some possible means of compensating thermal expansions must be provided, as explained hereinafter.
A further development of the invention thus allows for this purpose that the value of the tangent of angle a (FIG. 3) between the mutual lines of contact 4, 5 of the shroud plates and a straight line 8 cutting these edges of contact and running parallel to the turbine or compressor axis may be so chosen that it is greater than the coeflicient of friction between the surfaces of the contacting sides 6, '7 0f the shroud plates 2.
By giving the contacting lines 4, 5 of the shroud plates 2 a correspondingly large inclination to a straight line cutting these edges of contact and running parallel to the turbine or compressor axis and this in the assembled condition, i.e. a correspondingly large angle a is thus provided, the blades can twist against the pre-applied torsional stressing so that angle at diminishes, on thermal expansions appearing, by this means the distance apart of the contact lines 4 and 5 of the individual shroud plates, as projected on to the blading periphery, remains constant. At the same time it is guaranteed by the measurement of angle given above, that this twisting of the blades which compensates the thermal expansions is not reduced as a result of self-restraint by friction. If necessary the surfaces of contact 6, 7 of the shroud plates 2 can be treated by any known method, such as by chrome plating, for the reduction of friction or, resp., the easing of the compensating movements. A reduction of this type in the friction does not have a detrimental effect on the damping of the oscillations as by means of the arrangement as according to the invention the blade oscillations are not to be completely checked but correspondingly damped by friction.
The invention is not limited solely to the constructional example, it can, for example, be employed both for moving and guide blading.
What I claim is:
1. A shrouded bl-ading assembly for rotary machines such as turbines and compressors, each blade being composed of a material having an inherent property of recovery from torsional stressing forces imposed within the elastic limit of the material, each said blade including as an integral part thereof a shroud plate constituting its appertaining portion of the complete shroud ring established by the assembly of all blades, said shroud plates having the configuration of a parallelogram and with adjoining side faces thereof lying in contact with each other at an angle which is oblique to the axis of rotation of said machine, said blades being stressed torsionally from an unstressed condition by torsional flexure of the shank portions thereof carrying said shroud plates relative to the fixed root portions of the blades thereby to establish a continuous frictional pressure engagement between the adjoining side faces of said shroud plates brought about by the inherent tendency in the blading to recover its normal unstressed condition.
2. A shrouded blading assembly as defined in claim 1 wherein the tangent of said oblique angle is greater than the coetficient of friction existing between the adjoining side faces of said shroud plates.
References Cited by the Examiner UNITED STATES PATENTS 1,304,793 5/19 Moore 253-77 2,265,592 12/41 Allen 25377 2,398,140 4/46 Heppner 253-77 2,423,165 7/47 Allen 253-47 2,43 8,867 3/48 Rockwell et al 29-446 2,510,734 6/50 BOdger 253-77 JOSEPH H. BRANSON, JR., Primary Examiner.
WALTER BERLOWITZ, Examiner.

Claims (1)

1. A SHROUDED BLADING ASSEMBLY FO R ROTARY MACHINES SUCH AS TURBINES AND COMPRESSORS, EACH BLADE BEING COMPOSED OF A MATERIAL HAVING AN INHERENT PROPERTY OF RECOVERY FROM TORSIONAL STRESSING FORCES IMPOSED WITHIN THE ELASTIC LIMIT OF THE MATERIAL, EACH SAID BLADE INCLUDING AS AN INTEGRAL PART THEREOF A SHROUD PLATE CONSTITUTING ITS APPERTAINING PORTION OF THE COMPLETE SHROUD RING ESTABLISHED BY THE ASSEMBLY OF ALL BLADES, SAID SHROUD PLATES HAVING THE CONFIGURATION OF A PARALLELOGRAM AND WITH ADJOINING SIDE FACES THEREOF LYING IN CONTACT WITH EACH OTHER AT AN ANGLE WHICH IS OBLIQUE TO THE AXIS OF ROTATION OF SAID MACHINE, SAID BLADES BEING STRESSED TORSIONALLY FROM AN UNSTRESSED CONDITION BY TORSIONAL FLEXURE OF THE SHANK PORTIONS THEREOF CARRYING SAID SHROUD PLATES RELATIVE TO THE FIXED ROOT PORTIONS OF THE BLADES THEREBY TO ESTABLISH A CONTINUOUS FRICTIONAL PRESSURE ENGAGEMENT BETWEEN THE ADJOINING SIDE FACES OF SAID SHROUD PLATES BROUGHT ABOUT BY THE INHERENT TENDENCY IN THE BLADING TO RECOVER ITS NORMAL UNSTRESSED CONDITION.
US215617A 1961-08-10 1962-08-08 Shroud-blading for turbines or compressors Expired - Lifetime US3185441A (en)

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DEB63595A DE1159965B (en) 1961-08-10 1961-08-10 Device for vibration damping on a turbine or compressor blade ring

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GB (1) GB979392A (en)

Cited By (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3328867A (en) * 1962-07-11 1967-07-04 Bbc Brown Boveri & Cie Turbine blading
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
US3576377A (en) * 1967-12-22 1971-04-27 Rolls Royce Blades for fluid flow machines
JPS4930702A (en) * 1971-08-09 1974-03-19
US4211516A (en) * 1976-04-23 1980-07-08 Bbc Brown Boveri & Company Limited Blade structure for fluid flow rotary machine
US4332523A (en) * 1979-05-25 1982-06-01 Teledyne Industries, Inc. Turbine shroud assembly
US4533298A (en) * 1982-12-02 1985-08-06 Westinghouse Electric Corp. Turbine blade with integral shroud
US4722668A (en) * 1985-08-31 1988-02-02 Bbc Brown, Boveri & Company, Limited Device for damping blade vibrations in turbo-machines
US4986737A (en) * 1988-12-29 1991-01-22 General Electric Company Damped gas turbine engine airfoil row
US5083903A (en) * 1990-07-31 1992-01-28 General Electric Company Shroud insert for turbomachinery blade
US5120197A (en) * 1990-07-16 1992-06-09 General Electric Company Tip-shrouded blades and method of manufacture
US5238368A (en) * 1991-01-16 1993-08-24 Ortolano Ralph J Converting grouped blading to equivalent integral covered blading
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud
US5709527A (en) * 1995-02-17 1998-01-20 Abb Research Ltd. Vibration damping for turbine blades
WO2002025065A1 (en) * 2000-09-25 2002-03-28 Alstom (Switzerland) Ltd Seal system
US6454534B1 (en) 2000-12-21 2002-09-24 General Electric Company Flush bucket cover
WO2007000326A1 (en) * 2005-06-28 2007-01-04 Man Turbo Ag Turbine rotor and method for the production thereof
CH698087B1 (en) * 2004-09-08 2009-05-15 Alstom Technology Ltd Blade with shroud element.
US20130052020A1 (en) * 2011-08-23 2013-02-28 General Electric Company Coupled blade platforms and methods of sealing
EP2803821A1 (en) 2013-05-13 2014-11-19 Siemens Aktiengesellschaft Blade device, blade system, and corresponding method of manufacturing a blade system
US8974186B2 (en) 2010-07-12 2015-03-10 Man Diesel & Turbo Se Coupling element segments for a rotor of a turbomachine
US9127562B2 (en) 2009-09-18 2015-09-08 Man Diesel & Turbo Se Rotor of a turbomachine
US9752450B2 (en) 2015-06-04 2017-09-05 United Technologies Corporation Turbine engine tip clearance control system with later translatable slide block
US20180347381A1 (en) * 2017-05-30 2018-12-06 United Technologies Corporation Turbine blade including balanced mateface condition
US20190249555A1 (en) * 2016-12-22 2019-08-15 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1299004B (en) * 1965-01-19 1969-07-10 Bbc Brown Boveri & Cie Device for vibration damping on a turbine or compressor blade ring
DE2318059C3 (en) * 1973-04-06 1979-03-01 Kraftwerk Union Ag, 4330 Muelheim Multiple rotor blades for steam turbines with axial flow
DE3211073A1 (en) * 1982-03-25 1983-10-06 Kraftwerk Union Ag DEVICE FOR VIBRATION DAMPING ON A LEAD Vane
DE3802741C2 (en) * 1988-01-30 1997-02-13 Asea Brown Boveri Method of bracing blades
GB2215407A (en) * 1988-03-05 1989-09-20 Rolls Royce Plc A bladed rotor assembly
DE10014189A1 (en) 2000-03-23 2001-09-27 Alstom Power Nv Blade fastening for rotating machinery has blades fitted in slots without play or with pretensioning so that torsional moments acting on inner platform or blade roots oppose torsional moments acting upon outer platform or support wing
FR2825411B1 (en) * 2001-05-31 2003-09-19 Snecma Moteurs TURBINE DAWN WITH SEALING LECHETTE
CN109057870B (en) * 2018-08-07 2020-12-01 中国航发湖南动力机械研究所 Turbine blade assembly

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US1304793A (en) * 1919-05-27 Turbine-bucket
US2265592A (en) * 1939-01-16 1941-12-09 Allis Chalmers Mfg Co Turbine blade
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
US2423165A (en) * 1945-07-12 1947-07-01 Allis Chalmers Mfg Co Welded blade structure
US2438867A (en) * 1945-06-01 1948-03-30 United Aircraft Corp Method of assembling shrouds on impellers
US2510734A (en) * 1946-04-06 1950-06-06 United Aircraft Corp Turbine or compressor rotor

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US2310412A (en) * 1941-03-08 1943-02-09 Westinghouse Electric & Mfg Co Vibration dampener
FR1033197A (en) * 1951-02-27 1953-07-08 Rateau Soc Vibration dampers for mobile turbo-machine blades

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1304793A (en) * 1919-05-27 Turbine-bucket
US2265592A (en) * 1939-01-16 1941-12-09 Allis Chalmers Mfg Co Turbine blade
US2398140A (en) * 1943-12-08 1946-04-09 Armstrong Siddeley Motors Ltd Bladed rotor
US2438867A (en) * 1945-06-01 1948-03-30 United Aircraft Corp Method of assembling shrouds on impellers
US2423165A (en) * 1945-07-12 1947-07-01 Allis Chalmers Mfg Co Welded blade structure
US2510734A (en) * 1946-04-06 1950-06-06 United Aircraft Corp Turbine or compressor rotor

Cited By (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3328867A (en) * 1962-07-11 1967-07-04 Bbc Brown Boveri & Cie Turbine blading
US3576377A (en) * 1967-12-22 1971-04-27 Rolls Royce Blades for fluid flow machines
US3575523A (en) * 1968-12-05 1971-04-20 Us Navy Labyrinth seal for axial flow fluid machines
JPS4930702A (en) * 1971-08-09 1974-03-19
US4211516A (en) * 1976-04-23 1980-07-08 Bbc Brown Boveri & Company Limited Blade structure for fluid flow rotary machine
US4332523A (en) * 1979-05-25 1982-06-01 Teledyne Industries, Inc. Turbine shroud assembly
US4533298A (en) * 1982-12-02 1985-08-06 Westinghouse Electric Corp. Turbine blade with integral shroud
US4722668A (en) * 1985-08-31 1988-02-02 Bbc Brown, Boveri & Company, Limited Device for damping blade vibrations in turbo-machines
US4986737A (en) * 1988-12-29 1991-01-22 General Electric Company Damped gas turbine engine airfoil row
US5120197A (en) * 1990-07-16 1992-06-09 General Electric Company Tip-shrouded blades and method of manufacture
US5083903A (en) * 1990-07-31 1992-01-28 General Electric Company Shroud insert for turbomachinery blade
US5238368A (en) * 1991-01-16 1993-08-24 Ortolano Ralph J Converting grouped blading to equivalent integral covered blading
US5509784A (en) * 1994-07-27 1996-04-23 General Electric Co. Turbine bucket and wheel assembly with integral bucket shroud
US5709527A (en) * 1995-02-17 1998-01-20 Abb Research Ltd. Vibration damping for turbine blades
US20040012151A1 (en) * 2000-09-25 2004-01-22 Alexander Beeck Sealing arrangement
WO2002025065A1 (en) * 2000-09-25 2002-03-28 Alstom (Switzerland) Ltd Seal system
US6916021B2 (en) 2000-09-25 2005-07-12 Alstom Technology Ltd. Sealing arrangement
US6454534B1 (en) 2000-12-21 2002-09-24 General Electric Company Flush bucket cover
CH698087B1 (en) * 2004-09-08 2009-05-15 Alstom Technology Ltd Blade with shroud element.
US7654797B2 (en) 2004-09-08 2010-02-02 Alstom Technology Ltd Blade with shroud
WO2007000326A1 (en) * 2005-06-28 2007-01-04 Man Turbo Ag Turbine rotor and method for the production thereof
US20090116964A1 (en) * 2005-06-28 2009-05-07 Man Turbo Ag Turbine rotor and method for producing the rotor
US9127562B2 (en) 2009-09-18 2015-09-08 Man Diesel & Turbo Se Rotor of a turbomachine
US8974186B2 (en) 2010-07-12 2015-03-10 Man Diesel & Turbo Se Coupling element segments for a rotor of a turbomachine
US8888459B2 (en) * 2011-08-23 2014-11-18 General Electric Company Coupled blade platforms and methods of sealing
US20130052020A1 (en) * 2011-08-23 2013-02-28 General Electric Company Coupled blade platforms and methods of sealing
EP2803821A1 (en) 2013-05-13 2014-11-19 Siemens Aktiengesellschaft Blade device, blade system, and corresponding method of manufacturing a blade system
US9752450B2 (en) 2015-06-04 2017-09-05 United Technologies Corporation Turbine engine tip clearance control system with later translatable slide block
US20190249555A1 (en) * 2016-12-22 2019-08-15 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly
EP3521564A4 (en) * 2016-12-22 2019-11-06 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly
US10865648B2 (en) * 2016-12-22 2020-12-15 Mitsubishi Heavy Industries Compressor Corporation Turbine rotor blade assembly
US20180347381A1 (en) * 2017-05-30 2018-12-06 United Technologies Corporation Turbine blade including balanced mateface condition
US10480333B2 (en) * 2017-05-30 2019-11-19 United Technologies Corporation Turbine blade including balanced mateface condition

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DE1159965B (en) 1963-12-27
GB979392A (en) 1965-01-01
CH397722A (en) 1965-08-31
FR1330657A (en) 1963-06-21

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