US20140044550A1 - Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine - Google Patents

Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine Download PDF

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Publication number
US20140044550A1
US20140044550A1 US13/962,319 US201313962319A US2014044550A1 US 20140044550 A1 US20140044550 A1 US 20140044550A1 US 201313962319 A US201313962319 A US 201313962319A US 2014044550 A1 US2014044550 A1 US 2014044550A1
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US
United States
Prior art keywords
web
axial securing
rotor disk
securing element
securing elements
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.)
Abandoned
Application number
US13/962,319
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English (en)
Inventor
Felix Kern
Frank Stiehler
Stephan Klaen
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.)
MTU Aero Engines AG
Original Assignee
MTU Aero Engines AG
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 MTU Aero Engines AG filed Critical MTU Aero Engines AG
Assigned to MTU Aero Engines AG reassignment MTU Aero Engines AG ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: Kern, Felix, KLAEN, STEPHAN, STIEHLER, FRANK
Publication of US20140044550A1 publication Critical patent/US20140044550A1/en
Abandoned 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
    • 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
    • F01D5/3023—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses
    • F01D5/303—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot
    • F01D5/3038—Fixing blades to rotors; Blade roots ; Blade spacers of radial insertion type, e.g. in individual recesses in a circumferential slot the slot having inwardly directed abutment faces on both sides
    • 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
    • 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 present invention relates to a restraint mechanism for rotor blades of a turbo engine on a rotor disk, a method for axially securing rotor blades on a rotor disk of a turbo engine, and the turbo engine.
  • Rotor blades 1 which are arranged with their root 2 inserted into an axial groove 4 of a rotor disk 6 of a turbo engine, as illustrated in FIGS. 1 and 2 , are usually secured by a restraint mechanism in the axial direction.
  • a known restraint mechanism has a plurality of securing elements 8 , each of which is arranged in the groove 4 between the root 2 and the base of the groove.
  • Each securing element 8 has a web 10 to be placed in the grooves 4 and has two securing sections 12 , 14 extending away from the web 10 on the end, becoming wider with respect to the groove 4 , so that, when installed, they are in contact with a front disk area 16 and a rear disk area 18 .
  • the object of the invention is to create a restraint mechanism for rotor blades of a turbo machine on a rotor disk which will eliminate the aforementioned disadvantages and will permit a favorable transfer of force between the rotor blades and the rotor disk.
  • another object of the present invention is to create an improved method for axially securing rotor blades on a rotor disk of a turbo engine as well as a turbo engine having an improved means of axially securing rotor blades.
  • a restraint mechanism according to the invention for rotor blades of a turbo engine on a rotor disk having blade root receptacles for placement of the rotor blades has a plurality of axial securing elements, each of which has at least one web for positioning in a blade root receptacle.
  • each web has a retaining section at the end to establish a form-fitting design with a mating brace of an opposing axial securing element.
  • each of the securing elements is connected in a form-fitting manner to the securing element on the opposite side, they are supported mutually, thereby resulting in a torque-free outward transfer of force. Furthermore, a defined flow of force is ensured.
  • the securing elements can be installed from the front or from the rear, as seen in the axial direction, regardless of the direction of installation.
  • the retaining sections may be narrower than the blade root receptacles in the area of placement of the securing elements and may assume an installed position, which is different from a secured position.
  • the retaining sections When installed, the retaining sections are aligned as flatly and/or almost as flatly as the webs, so that the retaining sections and the webs have the same or almost the same height.
  • the retaining sections may be plastically deformable, in which case they are then bent out of the flat assembly position into the upright secured position.
  • the retaining sections are prestressed into their upright secured position and then can be deformed elastically out of this position and into the flat assembly position. In this way, accidentally damaged securing elements can be replaced at any time, so that corresponding repairs can be performed rapidly.
  • the mating braces are preferably offset in the vertical direction of the securing elements and have an elongated shape extending in the transverse direction of the securing elements, where they have an extent such that, when installed, they extend beyond at least one neighboring blade root receptacle and/or they bridge a neighboring blade root receptacle.
  • the mating braces are therefore always situated in the secured position and need not first be moved into this position.
  • the mating braces run onto the rotor disk in assembly and thus define a definite axial securing position of the securing elements in the blade root receptacles.
  • two securing elements form a securing element pair.
  • Preferred securing elements each have a web from which a mating brace extends on one side in the transverse direction.
  • Each of the two securing elements of this pair has the same, i.e., identical, L-shaped design.
  • Two neighboring rotor blades can be secured quickly and reliably in this way.
  • the pair of securing elements may be used as a repair part, for example, when a traditional web-type securing element has been damaged. The defective securing element and a neighboring securing element can be removed and replaced by a pair of securing elements.
  • the restraint mechanism may also have at least one pair of securing elements, such that one securing element has a web with a mating brace extending on both sides of the web, while the other securing element has two webs spaced a distance apart from one another, connected by a mating brace.
  • one securing element has a web with a mating brace extending on both sides of the web
  • the other securing element has two webs spaced a distance apart from one another, connected by a mating brace.
  • Three neighboring rotor blades can be secured on the rotor disk by the U-shaped securing element and the T-shaped securing element, so that the restraint mechanism may be used with rotor disks having an even number of rotor blades or used with rotor disks having an odd number of rotor blades in the combination of the two pairs of securing elements (2 L-shaped securing elements yield one pair of securing elements, 1 T-shaped securing element and 1 U-shaped securing element yield a pair of securing elements).
  • the pair of securing elements consisting of the U-shaped securing element and the T-shaped securing element with an odd number of rotor blades may be used more or less as the closure of the restraint mechanism.
  • the securing elements do not form a self-contained pair of securing elements but instead identical securing elements are assembled in a chain.
  • Preferred securing elements to form the securing element chain each have a U-shaped design and have two webs joined together by a mating brace and spaced a distance apart from one another, so that two securing elements may be placed with one of their two webs between the webs.
  • each securing element extends over four rotor blades.
  • a U-shaped securing element and an I-shaped securing element may be provided, each being installed one or more times.
  • the I-shaped securing element has a body section, which is wider than the respective blade root receptacle in the placement area of the securing element and is free of engagement of a retaining section when installed.
  • the I-shaped securing element is positioned between two U-shaped securing elements having the same orientation, so that the opposite U-shaped securing element has a widened mating brace, so that three webs may be placed between its two webs.
  • the respective form-fitting design can be improved and/or manufactured more simply if the retaining sections each have a catch nose with dimensional stability for reaching around the respective mating brace in some sections.
  • axial securing elements are inserted into the blade root receptacles and are interconnected by at least one form-fitting design.
  • the securing elements are each connected to a securing element on the opposite side and are thus mutually supported, so that there is a transfer of force to the outside without any torque. Furthermore, a defined flow of force is ensured.
  • the mutual support can be further improved if the securing elements are connected to one another by a mutual form-fitting design.
  • a preferred turbo engine has a bladed rotor disk, whose rotor blades are inserted into their blade root receptacles and are secured in the axial direction by a restraint mechanism according to the invention.
  • FIGS. 1 and 2 show a known axial means of securing a rotor blade on a rotor
  • FIG. 3 shows an assembly diagram of a pair of securing elements of a restraint mechanism according to the invention
  • FIG. 4 shows a single diagram of an L-shaped axial securing element of the pair of securing elements
  • FIG. 5 shows an exploded diagram of a pair of securing elements having a U-shaped securing element and a T-shaped securing element
  • FIG. 6 shows an assembly diagram of a chain of securing elements of a restraint mechanism according to the invention
  • FIG. 7 shows a single diagram of a U-shaped axial securing element of the chain of securing elements.
  • FIG. 8 shows an exploded diagram of a pair of securing elements having a lengthened U-shaped securing element and an I-shaped securing element.
  • FIG. 3 shows a securing element pair 20 of a restraint mechanism according to the invention for axially securing rotor blades (not shown) on a rotor disk (not shown).
  • the root of each rotor blade is inserted into an axial blade root receptacle and/or a rotor groove on the rotor disk.
  • the rotor blades are secured radially in the rotor grooves by a form-fitting contour of the rotor grooves and roots.
  • the restraint mechanism has a plurality of securing element pairs 20 , in this embodiment each having two identical axial securing elements 22 , 22 ′, each forming mutually a form-fitting connection.
  • the securing elements 22 , 22 ′ have, as in FIG. 4 for the securing element 22 , for example, a web 24 , which has a retaining section 26 on the end and a mating brace 28 on the end.
  • the web 24 has a plate-type contour and extends in the transverse direction y and/or has a width corresponding to the rotor groove in the placement area of the securing element 22 .
  • the web 24 thus has mainly a width that is equal to or narrower than the base of a groove.
  • the mating brace 28 is designed to be rigid and is arranged with an offset in the vertical direction z with respect to the web 24 . It has an elongated extent in the transverse direction y of the securing element 22 and therefore has an elongated extent in the circumferential direction of the rotor disk. It is thus arranged at a distance from the web 24 in the vertical direction z and is designed as a one-sided arm in the exemplary embodiment shown here. It has an extent in the transverse direction y such that it bridges a neighboring rotor groove.
  • the retaining section 26 is plastically deformable and is set back at one end in comparison with the flanks of the web which are not labeled with numbers. It is thus narrower than the rotor groove in the placement area of the securing element 22 . It can be converted from a shallow assembly position to the upright securing position shown here. Due to the narrow design and the flat assembly position of the retaining section 26 , the rotor disk can be bladed before the securing elements 22 are inserted into the rotor grooves because the retaining section 26 can be pushed between the base of the groove and the blade roots.
  • the retaining section 26 preferably has a catch nose 30 to form a radially outer bordering face for a mating brace 28 ′ of a neighboring securing element 22 ′ (see FIG. 3 ).
  • two securing elements 22 , 22 ′ When installed on the rotor disk, two securing elements 22 , 22 ′ are each oriented so they are offset in relation to one another in the axial direction x. With their webs 24 , 24 ′ they each pass through a rotor groove and are in contact with a front side face and/or a rear side face of the rotor disk with their mating braces 28 , 28 ′.
  • the mating braces 28 , 28 ′ are offset in relation to one another in the circumferential direction of the rotor disk and they each bridge the rotor groove in which the web 24 , 24 ′ of the opposite securing element 22 , 22 ′ is placed and/or protrudes and/or out of which the retaining section 26 , 26 ′ of the opposite securing element 22 , 22 ′ protrudes.
  • the retaining sections 26 , 26 ′ are shaped around the mating brace 28 , 28 ′ of the opposite securing element 26 , 26 ′ until the latter extend around the mating braces 28 , 28 ′ with their catch noses 30 , 30 ′.
  • the securing elements 22 , 22 ′ are then joined to one another mutually by a form-fitting design and the rotor blades placed in these rotor grooves are releasably secured on the rotor disk in the axial direction.
  • the rotor blades are double secured. If, for example, the retaining section 26 is inadvertently released from the form-fitting design with the mating brace 28 ′ or even breaks away from it, the respective rotor blade is still axially secured by the mating brace 28 ′ bridging the rotor groove.
  • a securing element pair 32 is provided; three rotor blades can be secured on one rotor disk by this pair.
  • This securing element pair 32 consists of two different securing elements 34 , 36 , namely a T-shaped securing element 34 and a U-shaped securing element 36 , which are installed opposite one another in the axial direction x.
  • the T-shaped securing element 34 has a web 24 which is placed at the center of a mating brace 28 .
  • the mating brace 28 thus extends on both sides of the web 24 and more or less has two arm halves 38 , 40 .
  • the arm halves 38 , 40 have an extent in the transverse direction y, such that, when installed, they each bridge a neighboring rotor groove.
  • the web 24 has a plastically deformable retaining section 26 with one catch nose 30 .
  • the securing element 36 is designed in a U-shaped design with two webs 24 ′ spaced a distance apart from one another in the transverse direction y, each having a retaining section 26 ′ with a catch nose 30 ′ and being connected to one another via a mating brace 28 ′.
  • the webs 24 ′ are spaced a distance apart from one another so that, when installed, they are not accommodated in the respective neighboring rotor groove but instead in the next-but-one rotor groove. In other words, when installed, an empty groove is formed between the webs to receive the web 24 of the T-shaped securing element 34 .
  • the T-shaped securing element 34 and the U-shaped securing element 36 are oriented oppositely from one another in the axial direction x. With their webs 24 , 24 ′ they each sit in a rotor groove and are in contact at their mating braces 28 , 28 ′ with a front side face and/or a rear side face of the rotor disk.
  • the T-shaped securing element 34 is placed with its web 24 in the empty groove between the webs 24 ′ of the U-shaped securing element.
  • the retaining sections 26 , 26 ′ are placed around the mating braces 28 ′, 28 and/or the mating braces 28 ′ and the arm halves 38 , 40 of the opposite securing element 36 , 34 , which are thereby connected to one another by their mutual form-fitting design.
  • FIG. 6 shows a securing element chain 42 of a restraint mechanism according to the invention.
  • the securing element chain 42 is characterized in that a securing element 44 ′ is connected in a mutually form-fitting manner to both of its neighboring securing elements 44 , 44 ′′, so that the restraint mechanism is closed in a ring shape around the circumference of the rotor disk.
  • the securing elements 44 , 44 ′, 44 ′′ are identical and have a U-shaped design, as shown clearly by the securing element 44 in FIG. 7 , for example. They each have two webs 24 spaced a distance apart from one another in the transverse direction y, each of them having a retaining section 26 with a catch nose 30 and connected to one another by a mating brace 28 . However, in contrast with the U-shaped securing element 36 according to FIG. 5 , the webs 24 with the securing elements 44 , 44 ′, 44 ′′ are spaced so far apart from one another that, when installed, not just one empty groove but two free empty grooves each are formed between them. The U-shaped securing elements 44 , 44 ′, 44 ′′ thus each extend over four rotor blades.
  • two of the U-shaped securing elements 44 , 44 ′′ are arranged side by side with the same orientation in the axial direction x when installed on the rotor disk.
  • a third U-shaped securing element 44 ′ is oriented in the axial direction x opposite the two U-shaped securing elements 44 , 44 ′′ which are oriented in the same way.
  • the opposite securing element 44 ′ bridges with its mating brace 28 ′ two empty grooves in which the identically oriented securing elements 44 , 44 ′′ are each arranged with one web 24 , 24 ′′.
  • the retaining sections 26 , 26 ′, 26 ′′ are placed in a form-fitting manner around the respective mating braces 28 , 28 ′, 28 ′′ of the securing elements 44 , 44 ′, 44 ′′ and are thus connected to same by a mutual form-fitting design. This placement is continued until the securing element chain 42 is closed.
  • a securing element pair 46 shown in FIG. 8 is installed one or more times as a closure, because in the case of blade numbers not divisible by four (4), at least one empty groove is formed between the securing elements 44 , 44 ′′ on the end and is aligned equally in the axial direction x.
  • the securing elements 44 , 44 ′′ on the end are thus spaced a distance apart from one another in the circumferential direction and can no longer be connected to an identical securing element 44 ′ because its mating brace 28 ′ has a transverse extent y that is too short.
  • the securing element pair 46 thus comprises a U-shaped securing element 48 , whose two webs 24 ′ are spaced a distance apart from one another, such that its mating brace 28 ′ may extend over three empty grooves.
  • the U-shaped securing element 48 is thus broadened in the transverse direction y in comparison with the U-shaped securing elements 44 , 44 ′, 44 ′′ according to FIGS. 6 and 7 .
  • the webs 24 ′ each have a retaining section 26 ′ with a catch nose 30 ′ at the end.
  • the securing element pair 46 has an approximately I-shaped securing element 50 .
  • the I-shaped securing element 50 has a web 24 ′′ which has a retaining section 26 ′ with a catch groove 30 ′′′.
  • the I-shaped securing element 50 has a body section 52 at the end.
  • the body section 52 is arranged with an offset in the vertical direction z in comparison with the web 24 ′′ and has an extent on both sides of the web 24 ′′ such that, when installed, it is in contact with the side faces of the rotor disk.
  • the widened U shape securing element 48 When installed, the widened U shape securing element 48 is oriented in the axial direction x opposite the U-shaped securing elements 44 , 44 ′′ at the ends and bridges the empty groove.
  • the retaining sections 26 ′, 26 ′ of the widened U-shaped securing element 48 reach around the mating braces 28 , 28 ′′ of the securing elements 44 , 44 ′′ on the ends.
  • the retaining sections 26 , 26 ′′ of the securing elements 44 , 44 ′′ on the ends reach around the mating brace 28 ′ of the widened U-shaped securing element 48 with their catch noses 30 , 30 ′′.
  • the securing elements 44 , 44 ′′, 48 are now situated in mutual form-fitting engagement.
  • the I-shaped securing element 50 is inserted into the empty groove opposite the widened U-shaped securing element 48 . With its body section 52 , it is then in contact at the sides with the empty groove on the side faces of the rotor disk, and it extends around the mating brace 28 ′ of the U-shaped securing element 48 in a form-fitting manner with its retaining section 26 ′′′ and its catch nose 30 ′′′.
  • the securing elements 22 , 34 , 36 , 44 , 48 , 50 are each made of a metallic material, i.e., a metal alloy.
  • the mating braces 28 are preferably curved according to the rotor disk in the transverse direction y of the securing elements and thus also in the circumferential direction of the restraint mechanism and/or the rotor disk.
  • the present invention discloses a restraint mechanism for rotor blades of a turbo engine on a rotor disk, which has blade root receptacles for radial guidance of the rotor blades, having a plurality of axial securing elements, each having at least one web for positioning in one blade root receptacle such that each web has a retaining section at the end for establishing a form-fitting design to a mating brace of a different axial securing element, as well as a method for axially securing rotor blades on a rotor disk and a turbo engine.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
US13/962,319 2012-08-09 2013-08-08 Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine Abandoned US20140044550A1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
EP12179777.3 2012-08-09
EP12179777.3A EP2696035A1 (de) 2012-08-09 2012-08-09 Rückhaltevorrichtung für Laufschaufeln einer Strömungsmaschine und zugehöriges Montageverfahren

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US20140044550A1 true US20140044550A1 (en) 2014-02-13

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US13/962,319 Abandoned US20140044550A1 (en) 2012-08-09 2013-08-08 Restraint Mechanism for Rotor Blades of a Turbo Engine, an Assembly Method and a Turbo Engine

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Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130149127A1 (en) * 2011-12-09 2013-06-13 General Electric Company Structural Platforms for Fan Double Outlet Guide Vane
US9303531B2 (en) 2011-12-09 2016-04-05 General Electric Company Quick engine change assembly for outlet guide vanes
US9303520B2 (en) 2011-12-09 2016-04-05 General Electric Company Double fan outlet guide vane with structural platforms
US10724390B2 (en) 2018-03-16 2020-07-28 General Electric Company Collar support assembly for airfoils
CN114483202A (zh) * 2021-12-17 2022-05-13 中国航发湖南动力机械研究所 一种用于长伸根、带冠互锁叶片的限位组件和涡轮转子

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DE102013205948B4 (de) * 2013-04-04 2015-03-12 MTU Aero Engines AG Sicherungssystem und Verfahren zur Sicherung eines Befestigungsbereichs wenigstens einer Rotorschaufel oder eines Rotorschaufelsegments in einem Montagebereich eines Rotorgrundkörpers

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US3057598A (en) * 1960-07-01 1962-10-09 Ass Elect Ind Locking means for turbine or compressor blading
US6190131B1 (en) * 1999-08-31 2001-02-20 General Electric Co. Non-integral balanced coverplate and coverplate centering slot for a turbine

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130149127A1 (en) * 2011-12-09 2013-06-13 General Electric Company Structural Platforms for Fan Double Outlet Guide Vane
US9303531B2 (en) 2011-12-09 2016-04-05 General Electric Company Quick engine change assembly for outlet guide vanes
US9303520B2 (en) 2011-12-09 2016-04-05 General Electric Company Double fan outlet guide vane with structural platforms
US10724390B2 (en) 2018-03-16 2020-07-28 General Electric Company Collar support assembly for airfoils
CN114483202A (zh) * 2021-12-17 2022-05-13 中国航发湖南动力机械研究所 一种用于长伸根、带冠互锁叶片的限位组件和涡轮转子

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