US2935296A - Blade retaining means - Google Patents

Blade retaining means Download PDF

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Publication number
US2935296A
US2935296A US263436A US26343651A US2935296A US 2935296 A US2935296 A US 2935296A US 263436 A US263436 A US 263436A US 26343651 A US26343651 A US 26343651A US 2935296 A US2935296 A US 2935296A
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Prior art keywords
blade
foot
pin
slot
rotor
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Expired - Lifetime
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US263436A
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Chester E Hockert
Leslie R Smith
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Motors Liquidation Co
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Motors Liquidation Co
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Priority to US263436A priority Critical patent/US2935296A/en
Priority to GB32692/52A priority patent/GB723405A/en
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Publication of US2935296A publication Critical patent/US2935296A/en
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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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/32—Locking, e.g. by final locking blades or keys
    • F01D5/326—Locking of axial insertion type blades by other means
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections

Definitions

  • This invention relates to blading of a type suitable for use in elastic tiuid machines such as axial tiow compressors and turbines and the like and has for its purpose the provision of a simple and inexpensive blade retaining means which efliciently secures a footed blade against movement in a blade carrying member and which greatly facilitates removal of a damaged blade without damage to the blade carrying member.
  • a footed blade is secured against movement in a slot contained in a blade carrying member by a retaining pin extending between the blade carrying member and the foot of the blade.
  • the pin is constructed from soft material so as to be sheared off when the blade is driven from the slot for removal. This results in freezing of the pin in the blade carrying member and may necessitate drilling to effect removal of the pin which oftentimes results in damage to the blade carrying member.
  • the retaining pin is formed from material having a high shear strength, preferably greater than the foot of the blade and the location of the pin with respect to the end of the blade foot in such that, when removal of a damaged blade becomes necessary, a portion of the foot of the blade may be broken otf readily without shearing or damaging the pin, thereby releasing the blade foot from the pin and facilitating removal of both the blade and pin without damage to the blade carrying member.
  • the principal objects of the invention are to provide an improved structure for bladed machines such as compressors and to facilitate the removal of damaged blades therefrom.
  • Figure l is a fragmentary longitudinal sectional view of an axial flow compressor employing blade retaining means in accordance with the invention
  • Figure 2 is a fragmentary detail sectional View of a retaining means in accordance with the invention in the same plane as Fig. l
  • Figure 3 is a fragmentary transverse sectional view taken in the plane 3 3 of Figure 2
  • Figure 4 is a View illustrating removal of a blade in accordance with the invention.
  • the invention is shown embodied in the rotor of an axial-flow compressor of a type employed in gas turbine aircraft jet engines. Only a portion of the compressor is shown, the remainder of the engine being omitted in the interest of clarity of the drawings and conciseness of the specification, since the general structure of such an engine is well understood by those skilled in the art.
  • the compressor shown in Figure l is of the multi stage type and comprises a casing or stator 1t) which mounts a number of rows of stator vanes i2 and a rotor member mounted on a shaft (not shown) and defined ICC by a plurality of axially spaced rotor disks 14 each having a number of rotor blades 16 mounted about the circumference thereof.
  • the compressor casing is formed by a pair of semicylindrical sections which are fastened together by means of anges (not shown) provided along the sides thereof.
  • the stator vanes 12 of each stator stage are mounted between outer and inner shroud bands 18 and 2b, both of which are constituted by a pair of semi-circular segments corresponding to the halves of the casing 10.
  • the outer shroud band 18 is seated in a groove 22 in the inner surface of the casing, and retained in a suitable manner (not shown).
  • the inner shroud band 20 comprises a pair of concentric channel members 24, 26 having superimposed webs, which may be spot welded together, and inwardly directed tlanges.
  • the outer shroud band 18 and the inner shroud band 2t) function principally to support and radially space the stator vanes 12, the inner shroud band serving further to provide an elfective fluid seal between the stationary and moving parts of the compressor.
  • the ends of the stator vanes are shaped to provide projecting tangs or tenons 28 which are received in apertures in the shroud bands.
  • the tenions are headed, welded, or brazed to secure the vanes 12 to the shroud bands.
  • the rotor disks 14, which are mounted for rotation in known manner on a stub shaft (not shown) journaled within the compressor casing are each constituted by a thickened rim 30 and a spacing ring or flange 32 integrally formed thereon and extending rearwardly therefrom.
  • the after end 34 of the spacing ring of each rotor disk engages a mating shoulder 36 formed in the forward edge of the rim of the succeeding rotor disk.
  • the rotor disks are coupled by a number of short dowel pins 3S which extend parallel to the axis of the compressor and are closely fitted in holes 40 circumferentially spaced about the edge of the spacing ring.
  • a number of similar openings 42 are provided in the forward edge of each rotor wheel rim to receive the pins 38 extending from the spacing ring.
  • the pins 38 serve to lock the rotor wheels against rotational movement relative to one another and to transmit torque therebetween.
  • the disks are held assembled by a tie bolt (not shown) extending between the hubs of the end disks of the assembly in known manner.
  • the rotor blades 16 are provided with an integrally formed foot 44 which is received in one of a plurality of mating dovetail slots 46 formed in and spaced about the periphery of the rim 30 of each rotor wheel.
  • a transverse slot 4S (Figs. 2 and 3) is formed intermediate the ends of the foot of the blade to receive a retaining pin 50 which is driven through a hole 52 in the after portion of the wheel rim after a blade is located in its slot, whereby a simple, etiicient, positive lock is provided between the blade and the rotor rim.
  • the pin is retained by friction in the hole 52.
  • the foot recess 48 may extend transversely across the base of the foot of the blade and is preferably located a short distance from the downstream end of the blade foot.
  • the rim of the rotor disk and the pin 50 are preferably of a strong material such as alloy steel.
  • the blade foot may be of a more easily fractured or broken material. in any event, the size of the pin 50 and the thickness of the lip 54 on the blade foot behind the slot 48 may be so proportioned that if the blade is driven forward in the slot, the lip 54 will be broken off without bending or damaging the pin.
  • Fig. 4 The removal of the blade by breaking the frangible lip 54 is illustrated in Fig. 4.
  • the pin Si may be driven or pressed out preparatory to inserting a new blade. While the removal operation damages the blade, this is immaterial, as the blades are Y 3 not ordinarily removed unless they have been damaged. The removal of the undamaged pin does not damage the rotor.
  • V bladede 'root groove has a substantial radial component due to the taper of the rotor surface, as particularly appears in the left-handV disk of Fig. 1,V centrifugal force urges the blade rearwardly; This force is exerted against the'pin 50 by the main-body of the root, which is easily capable of taking this load.
  • a blade having a foot having axially extending sides and transversely extending ends, a blade carrying member containing a mating axially extending slot for slidably receiving said blade foot, the blade foot having a recess formed therein adjacent one end thereof, and means for retaining said blade in said slot comprising a pin inserted from said blade carrying member to engage Y within the recess Vin said blade foot, the pin being more resistant to fracture than the portion of the blade foot between said recess and said one end, whereby the said portion of said blade foot may be readily broken oi to free said blade of said pin for removal of the blade.
  • a blade having a foot having axially extending sides and transversely extending ends, a blade carrying member containing a mating axially extending slot for receiving said blade foot, means for retaining said blade against movement in said slot comprising a pin inserted through said blade carrying member to engage a recess located in said blade foot ⁇ and adjacent one of the ends of the foot of said blade and the corresponding end of said slot, said recess extending transversely thereacross, said retaining pin having a shear strength greater than that of said blade foot, whereby a portion of said blade foot may be readily broken oi to free said blade of said pin for removal of the blade.
  • a footed blade a rotor member having a tapered surface and containing a mating slot for cated near the end of said blade toward which the blade is urged by said component of centrifugal'force, said pin being more resistantfto shear fracture than a portion of the blade foot on one side of said recess whereby the said portion of said blade foot may be readily broken o to free said blade of said pin for removal of the blade.
  • a blade having a frangible foothaving axially extending sides and transversely extending ends with an undercut portion thereon adjacent one end thereof, a blade carrying member having a slot therein receiving said blade foot and a relatively infrangible pin inserted from said blade carrying member to engage the said undercut portion of said blade foot in said slot.
  • a footed blade having an undercut bottom portion forming a narrow lip with a part of the Y blade foot on one side of the undercut portion thereof
  • said blade having a component Y the thickness of said lip measured in a generally axial direction of the blade being several times less than that of the part of said blade foot on the other side of said undercut portion, a blade carrying, member, having a slot therein for receiving said blade foot and a pin inserted from. said blade carrying member to engage the said undercut portion of saidV blade foot for retaining said blade, in said slot.
  • a rotor blade havingranV enlarged foot thereon and containing an aperture' therein, a support member having a slot therein forreceiving the foot of said blade, and a pin-like member carried by said support member and engaging the aperture in said blade foot to retain said blade in said slot, the aperture in said blade foot being displaced from the center of the blade toward one end of the blade foot and slot and the pin-like member being of higher resistance to shear fracture than the part of said bladerfoot between the aperture and the end of the blade foot adjacent said aperture, whereby the blade can be destructibly released from said support member by sliding the blade longitudinally of the slot thereby causing the pin to shear the said part of the blade foot.

Description

May 3, 1960 c. E. HocKERT ETAL 2,935,296
BLADE RETAINING MEANS Filed Dec. 2e, 1951 v fw -v L INVENTORS.
87 MMSLM,
R/VEKSZ BLADE RETAJNING MEANS Chester E. Hockert and Leslie R. Smith, Indianapolis, ind., assigner-s to General Motors Corparation, a cor'- poration of Delaware Application December 26, 1951, Serial No. 263,436
6 Claims. (Cl. 253-77) This invention relates to blading of a type suitable for use in elastic tiuid machines such as axial tiow compressors and turbines and the like and has for its purpose the provision of a simple and inexpensive blade retaining means which efliciently secures a footed blade against movement in a blade carrying member and which greatly facilitates removal of a damaged blade without damage to the blade carrying member.
ln one form of blade retaining means which has been proposed heretofore, a footed blade is secured against movement in a slot contained in a blade carrying member by a retaining pin extending between the blade carrying member and the foot of the blade. The pin is constructed from soft material so as to be sheared off when the blade is driven from the slot for removal. This results in freezing of the pin in the blade carrying member and may necessitate drilling to effect removal of the pin which oftentimes results in damage to the blade carrying member.
ln accordance with the present invention, the retaining pin is formed from material having a high shear strength, preferably greater than the foot of the blade and the location of the pin with respect to the end of the blade foot in such that, when removal of a damaged blade becomes necessary, a portion of the foot of the blade may be broken otf readily without shearing or damaging the pin, thereby releasing the blade foot from the pin and facilitating removal of both the blade and pin without damage to the blade carrying member.
The principal objects of the invention are to provide an improved structure for bladed machines such as compressors and to facilitate the removal of damaged blades therefrom.
The preferred manner in which these objects of the invention are realized together with the features and advantages attending the invention, will appear more fully from the following detailed description and drawings, wherein; Figure l is a fragmentary longitudinal sectional view of an axial flow compressor employing blade retaining means in accordance with the invention; Figure 2 is a fragmentary detail sectional View of a retaining means in accordance with the invention in the same plane as Fig. l; Figure 3 is a fragmentary transverse sectional view taken in the plane 3 3 of Figure 2; and Figure 4 is a View illustrating removal of a blade in accordance with the invention.
Referring to the drawings, the invention is shown embodied in the rotor of an axial-flow compressor of a type employed in gas turbine aircraft jet engines. Only a portion of the compressor is shown, the remainder of the engine being omitted in the interest of clarity of the drawings and conciseness of the specification, since the general structure of such an engine is well understood by those skilled in the art.
The compressor shown in Figure l is of the multi stage type and comprises a casing or stator 1t) which mounts a number of rows of stator vanes i2 and a rotor member mounted on a shaft (not shown) and defined ICC by a plurality of axially spaced rotor disks 14 each having a number of rotor blades 16 mounted about the circumference thereof.
The compressor casing is formed by a pair of semicylindrical sections which are fastened together by means of anges (not shown) provided along the sides thereof. The stator vanes 12 of each stator stage are mounted between outer and inner shroud bands 18 and 2b, both of which are constituted by a pair of semi-circular segments corresponding to the halves of the casing 10. The outer shroud band 18 is seated in a groove 22 in the inner surface of the casing, and retained in a suitable manner (not shown). The inner shroud band 20 comprises a pair of concentric channel members 24, 26 having superimposed webs, which may be spot welded together, and inwardly directed tlanges. The outer shroud band 18 and the inner shroud band 2t) function principally to support and radially space the stator vanes 12, the inner shroud band serving further to provide an elfective fluid seal between the stationary and moving parts of the compressor. The ends of the stator vanes are shaped to provide projecting tangs or tenons 28 which are received in apertures in the shroud bands. The tenions are headed, welded, or brazed to secure the vanes 12 to the shroud bands.
The rotor disks 14, which are mounted for rotation in known manner on a stub shaft (not shown) journaled within the compressor casing are each constituted by a thickened rim 30 and a spacing ring or flange 32 integrally formed thereon and extending rearwardly therefrom. The after end 34 of the spacing ring of each rotor disk engages a mating shoulder 36 formed in the forward edge of the rim of the succeeding rotor disk. The rotor disks are coupled by a number of short dowel pins 3S which extend parallel to the axis of the compressor and are closely fitted in holes 40 circumferentially spaced about the edge of the spacing ring. A number of similar openings 42 are provided in the forward edge of each rotor wheel rim to receive the pins 38 extending from the spacing ring. The pins 38 serve to lock the rotor wheels against rotational movement relative to one another and to transmit torque therebetween. The disks are held assembled by a tie bolt (not shown) extending between the hubs of the end disks of the assembly in known manner.
As best shown in Figure 3, the rotor blades 16 are provided with an integrally formed foot 44 which is received in one of a plurality of mating dovetail slots 46 formed in and spaced about the periphery of the rim 30 of each rotor wheel. For the purpose of securing the blade against movement in the dovetail slot, a transverse slot 4S (Figs. 2 and 3) is formed intermediate the ends of the foot of the blade to receive a retaining pin 50 which is driven through a hole 52 in the after portion of the wheel rim after a blade is located in its slot, whereby a simple, etiicient, positive lock is provided between the blade and the rotor rim. The pin is retained by friction in the hole 52.
The foot recess 48 may extend transversely across the base of the foot of the blade and is preferably located a short distance from the downstream end of the blade foot.
The rim of the rotor disk and the pin 50 are preferably of a strong material such as alloy steel. The blade foot may be of a more easily fractured or broken material. in any event, the size of the pin 50 and the thickness of the lip 54 on the blade foot behind the slot 48 may be so proportioned that if the blade is driven forward in the slot, the lip 54 will be broken off without bending or damaging the pin.
The removal of the blade by breaking the frangible lip 54 is illustrated in Fig. 4. After the blade is driven out, the pin Si) may be driven or pressed out preparatory to inserting a new blade. While the removal operation damages the blade, this is immaterial, as the blades are Y 3 not ordinarily removed unless they have been damaged. The removal of the undamaged pin does not damage the rotor.
Where the Vblade 'root groove has a substantial radial component due to the taper of the rotor surface, as particularly appears in the left-handV disk of Fig. 1,V centrifugal force urges the blade rearwardly; This force is exerted against the'pin 50 by the main-body of the root, which is easily capable of taking this load.
Even ifthe forces on the blade tend Vto slide it so as 'to load the lip 54, the latter can be made strong enough to accept the operating load, but to break when the blade root isY driven out for replacement.
There is thusrprovidedra simple and inexpensible blade retaining Ymeans which is not only simple to install and replace, but which also provides an efficient positive lock for securing a footed blade in a blade carrying member and` which greatly facilities removal of a damaged blade from itsslot without dmage to the blade carrying member. f Y
Although the present invention has been described with reference to one specific embodiment, it'will be understood that the invention is susceptible of embodiment in other forms. f
We claim: Y
l, In combination, a blade having a foot having axially extending sides and transversely extending ends, a blade carrying member containing a mating axially extending slot for slidably receiving said blade foot, the blade foot having a recess formed therein adjacent one end thereof, and means for retaining said blade in said slot comprising a pin inserted from said blade carrying member to engage Y within the recess Vin said blade foot, the pin being more resistant to fracture than the portion of the blade foot between said recess and said one end, whereby the said portion of said blade foot may be readily broken oi to free said blade of said pin for removal of the blade.
2. In combination, a blade having a foot having axially extending sides and transversely extending ends, a blade carrying member containing a mating axially extending slot for receiving said blade foot, means for retaining said blade against movement in said slot comprising a pin inserted through said blade carrying member to engage a recess located in said blade foot `and adjacent one of the ends of the foot of said blade and the corresponding end of said slot, said recess extending transversely thereacross, said retaining pin having a shear strength greater than that of said blade foot, whereby a portion of said blade foot may be readily broken oi to free said blade of said pin for removal of the blade.
3. In combination, a footed blade, a rotor member having a tapered surface and containing a mating slot for cated near the end of said blade toward which the blade is urged by said component of centrifugal'force, said pin being more resistantfto shear fracture than a portion of the blade foot on one side of said recess whereby the said portion of said blade foot may be readily broken o to free said blade of said pin for removal of the blade.
4. In combination, a blade having a frangible foothaving axially extending sides and transversely extending ends with an undercut portion thereon adjacent one end thereof, a blade carrying member having a slot therein receiving said blade foot and a relatively infrangible pin inserted from said blade carrying member to engage the said undercut portion of said blade foot in said slot.
5. In combination, a footed blade having an undercut bottom portion forming a narrow lip with a part of the Y blade foot on one side of the undercut portion thereof,
receiving said blade foot, said blade having a component Y the thickness of said lip measured in a generally axial direction of the blade being several times less than that of the part of said blade foot on the other side of said undercut portion, a blade carrying, member, having a slot therein for receiving said blade foot and a pin inserted from. said blade carrying member to engage the said undercut portion of saidV blade foot for retaining said blade, in said slot. e
6. In combination, a rotor blade havingranV enlarged foot thereon and containing an aperture' therein, a support member having a slot therein forreceiving the foot of said blade, and a pin-like member carried by said support member and engaging the aperture in said blade foot to retain said blade in said slot, the aperture in said blade foot being displaced from the center of the blade toward one end of the blade foot and slot and the pin-like member being of higher resistance to shear fracture than the part of said bladerfoot between the aperture and the end of the blade foot adjacent said aperture, whereby the blade can be destructibly released from said support member by sliding the blade longitudinally of the slot thereby causing the pin to shear the said part of the blade foot.
References Cited in the ile of this patent UNITED STATES PATENTS 741,776 Dodge Oct. 20, 1903 1,095,587 McIntosh May 5, 1914 1,535,417 Huff Apr. 28, 1925 1,959,220 Robinson May l5, 1934 2,483,610 Baumann Oct. 4, 1949
US263436A 1951-12-26 1951-12-26 Blade retaining means Expired - Lifetime US2935296A (en)

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GB32692/52A GB723405A (en) 1951-12-26 1952-12-24 Improvements in or relating to blade-carrying turbine rotors and the like

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Cited By (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3039740A (en) * 1959-11-27 1962-06-19 Gen Motors Corp Blade retainer
US3086697A (en) * 1958-05-12 1963-04-23 Ite Circuit Breaker Ltd Rotor design for aero-dynamic wave machine
US3291379A (en) * 1963-08-14 1966-12-13 Bbc Brown Boveri & Cie Pressure wave machine
US3295826A (en) * 1966-04-08 1967-01-03 Gen Motors Corp Blade lock
US3817655A (en) * 1972-11-22 1974-06-18 Carrier Corp Stator blade mounting structure for turbomachines
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly
US4489468A (en) * 1982-06-24 1984-12-25 Elliott Turbomachinery Co., Inc. Method of providing a multivalve turbine nozzle ring interface seal
US20090028712A1 (en) * 2005-12-10 2009-01-29 Mtu Aero Engines Gmbh Turbomachine having axial rotor blade securing
US20100322772A1 (en) * 2009-06-23 2010-12-23 Rolls-Royce Plc Annulus filler for a gas turbine engine
US20110038731A1 (en) * 2009-08-12 2011-02-17 Rolls-Royce Plc Rotor assembly for a gas turbine
US20110236185A1 (en) * 2010-03-23 2011-09-29 Rolls-Royce Plc Interstage seal
JP2014125047A (en) * 2012-12-26 2014-07-07 Kawasaki Heavy Ind Ltd Propeller blade fixing mechanism
US20140199172A1 (en) * 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
US20170241396A1 (en) * 2016-02-18 2017-08-24 Andritz Hydro Gmbh Pelton runner
WO2024010582A1 (en) * 2022-07-07 2024-01-11 Siemens Energy Global GmbH & Co. KG Coupling joints to interconnect and transmit rotational torque between adjacent impeller bodies in a turbomachine

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US741776A (en) * 1902-12-13 1903-10-20 Gen Electric Means for improving the efficiency of turbines.
US1095587A (en) * 1910-03-31 1914-05-05 George Mcintosh Turbine.
US1535417A (en) * 1924-07-05 1925-04-28 Ingersoll Rand Co Open impeller
US1959220A (en) * 1933-05-26 1934-05-15 Gen Electric Rotary disk turbine bucket wheel, or the like
US2483610A (en) * 1943-03-23 1949-10-04 Mini Of Supply Bladed impeller for turboblowers

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US741776A (en) * 1902-12-13 1903-10-20 Gen Electric Means for improving the efficiency of turbines.
US1095587A (en) * 1910-03-31 1914-05-05 George Mcintosh Turbine.
US1535417A (en) * 1924-07-05 1925-04-28 Ingersoll Rand Co Open impeller
US1959220A (en) * 1933-05-26 1934-05-15 Gen Electric Rotary disk turbine bucket wheel, or the like
US2483610A (en) * 1943-03-23 1949-10-04 Mini Of Supply Bladed impeller for turboblowers

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3086697A (en) * 1958-05-12 1963-04-23 Ite Circuit Breaker Ltd Rotor design for aero-dynamic wave machine
US3039740A (en) * 1959-11-27 1962-06-19 Gen Motors Corp Blade retainer
US3291379A (en) * 1963-08-14 1966-12-13 Bbc Brown Boveri & Cie Pressure wave machine
US3295826A (en) * 1966-04-08 1967-01-03 Gen Motors Corp Blade lock
US3817655A (en) * 1972-11-22 1974-06-18 Carrier Corp Stator blade mounting structure for turbomachines
US4265595A (en) * 1979-01-02 1981-05-05 General Electric Company Turbomachinery blade retaining assembly
US4489468A (en) * 1982-06-24 1984-12-25 Elliott Turbomachinery Co., Inc. Method of providing a multivalve turbine nozzle ring interface seal
US20090028712A1 (en) * 2005-12-10 2009-01-29 Mtu Aero Engines Gmbh Turbomachine having axial rotor blade securing
US20100322772A1 (en) * 2009-06-23 2010-12-23 Rolls-Royce Plc Annulus filler for a gas turbine engine
US8596981B2 (en) 2009-06-23 2013-12-03 Rolls-Royce Plc Annulus filler for a gas turbine engine
US20110038731A1 (en) * 2009-08-12 2011-02-17 Rolls-Royce Plc Rotor assembly for a gas turbine
US8636474B2 (en) * 2009-08-12 2014-01-28 Rolls-Royce Plc Rotor assembly for a gas turbine
US20110236185A1 (en) * 2010-03-23 2011-09-29 Rolls-Royce Plc Interstage seal
US8864451B2 (en) 2010-03-23 2014-10-21 Rolls-Royce Plc Interstage seal
JP2014125047A (en) * 2012-12-26 2014-07-07 Kawasaki Heavy Ind Ltd Propeller blade fixing mechanism
US20140199172A1 (en) * 2013-01-11 2014-07-17 General Electric Company Turbomachine and method of handling turbomachine components
US20170241396A1 (en) * 2016-02-18 2017-08-24 Andritz Hydro Gmbh Pelton runner
US10550821B2 (en) * 2016-02-18 2020-02-04 Andritz Hydro Gmbh Pelton runner
WO2024010582A1 (en) * 2022-07-07 2024-01-11 Siemens Energy Global GmbH & Co. KG Coupling joints to interconnect and transmit rotational torque between adjacent impeller bodies in a turbomachine

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