WO2021018333A1 - Module pour une turbomachine - Google Patents

Module pour une turbomachine Download PDF

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Publication number
WO2021018333A1
WO2021018333A1 PCT/DE2020/000175 DE2020000175W WO2021018333A1 WO 2021018333 A1 WO2021018333 A1 WO 2021018333A1 DE 2020000175 W DE2020000175 W DE 2020000175W WO 2021018333 A1 WO2021018333 A1 WO 2021018333A1
Authority
WO
WIPO (PCT)
Prior art keywords
component
segment
module
segments
joint
Prior art date
Application number
PCT/DE2020/000175
Other languages
German (de)
English (en)
Inventor
Stefan Rauscher
Manfred Feldmann
Peter Iberl
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
Publication of WO2021018333A1 publication Critical patent/WO2021018333A1/fr

Links

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
    • F01D5/12—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
    • 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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/26—Double casings; Measures against temperature strain in casings
    • 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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to a module for a turbomachine.
  • the turbo engine can be, for example, a jet engine, e.g. B. a turbofan engine.
  • the flow machine is functionally divided into a compressor, combustion chamber and turbine.
  • the air that is sucked in is compressed by the compressor and burned in the downstream combustion chamber with the added kerosene.
  • the resulting hot gas, a mixture of combustion gas and air flows through the downstream turbine and is expanded in the process.
  • Both the compressor and the turbine are generally constructed in several stages, each stage having a guide vane ring and a rotor blade ring.
  • the module in question here has a first and a second component, the components each extending circumferentially and segmented, that is to say being divided into a plurality of segments.
  • a segmentation is often used to store hotter components in a cool housing structure, the segment joints then absorbing differential thermal expansion.
  • the components have an axial overlap and such a radial offset that they rest against one another in a contact surface.
  • the first component can be, for example, a guide vane ring
  • the second component can be, for example, an outer air seal (OAS, Outer Air Seal). This is intended to illustrate the subject matter at hand, but not initially to limit its generality.
  • the present invention is based on the technical problem of specifying a particularly advantageous module for a turbomachine.
  • a segment joint of the first component and a segment joint of the second component are arranged in the same rotational position.
  • a first and a second segment of the first component adjoin each other with a joint edge located in the contact surface (at least in a state of thermal expansion), and in the segment joint of the second component a first and second segment of the second component (also each with an abutting edge located in the contact surface).
  • the abutting edge of the first segment of the first component runs in such a way that it forms an angle with the abutting edges of the first and second segments of the second component.
  • the joint edge of the first segment of the first component crosses the segment joint of the second component, that is to say the joint edges of the first and second segment thereof.
  • the first segment of the first component touches both the first and the second segment of the second component, ie is supported on both segments.
  • the abutting edge of the first segment of the first component can be prevented from getting caught on the abutting edge of the circumferentially opposite segment of the second component.
  • Such a blocked thermal expansion could otherwise be critical due to the increased loads.
  • an orientation of the joint edges not according to the invention for example, due to the tolerance situation, there could be no exact overlap of the segment joints with minimal thermal expansion and this could only arise at maximum thermal expansion.
  • the described hooking can occur.
  • a hooking could also be avoided by arranging the segment joints at different circumferential positions. However, this would mean an additional boundary condition that could require the component to be subdivided into more segments than is necessary for other technical reasons.
  • the axial overlap between the components consists of at least one axial section, so, for example, one component can also extend further axially forward than the other (in front of the overlap area) and / or the other component further axially backwards (behind the overlap area ).
  • the radial offset exists in the area of the axial overlap, where one component is arranged radially outside the other component when viewed in a section perpendicular to the axis.
  • the angle that the joint edge of the first segment of the first component makes with the joint edge of the first and second segment of the second component is based on the axially opening angle between the cutting lines (not the angle oriented in the direction of rotation).
  • the consideration of the joint edges refers to the contact surface and thus the area of the axial overlap; axially in front of or behind it, the segment joints can, for example, also have a different course (e.g. to reduce leakage).
  • the abutting edges In the area of the axial overlap, the abutting edges generally run in a straight line when viewed individually.
  • the abutting edges of the first and second segments of the first component are preferably parallel to one another; the same applies to the abutting edges of the first and second segments of the second component.
  • the angle enclosed by the abutting edges is at least 60 °, a preferred upper limit is at most 120 °. This also limits the inclination or inclination of the abutting edges, so for example acute-angled corners are avoided, which z. B. can reduce the risk of injury during assembly and revision. Angles of around 90 ° can be particularly preferred. In a preferred embodiment, not only the abutting edge of the first, but also the abutting edge of the second segment of the first component crosses both the abutting edge of the first and the second segment of the second component.
  • both joint edges of one component cross the segment joint of the other component, that is to say they touch the first and also the second segment of the first component both segments of the second component, i.e. both its first and its second (which is then very understandably also the other way around).
  • the inclination between the abutting edges of the first and second components can also be achieved, for example, if the abutting edges are tilted relative to the axial direction in only one of the components.
  • both the abutting edges of the first and second segment of the first component and the abutting edges of the first and second segment of the second component are preferably tilted relative to the axial direction, so the inclination is divided to a certain extent (e.g. avoidance of sharp corners).
  • the abutting edges of the first component with the axial direction preferably enclose an edge angle of at least 30 ° and at most 60 ° and / or the abutting edges of the first and second segment of the second component form an edge angle of at least 30 ° and at most with the axial direction 60 ° (the smaller of the two angles included with the axial direction is considered in each case).
  • “Majority” generally means at least two, so there are at least two segments per component. The number will preferably be higher, for example at least 4, 5 or 6 (a possible upper limit can be at most 100, for example).
  • the first and the second plurality can also be of the same size, ie the two components can have the same number of segments.
  • the two differ in their number of segments; the respective number of segments can be determined, for example, according to the structural-mechanical or production-technical boundary conditions of the respective component. Since the number of segments of the components does not need to be coordinated with one another, the total number of segments and thus the number of individual parts to be handled can be reduced. B. can be advantageous in terms of costs.
  • the rotary position at which the first and second segment of the first component and also the first and second segment of the second component adjoin one another is the only rotary position at which a segment joint of the first component meets a segment joint of the second component .
  • the remaining segment joints of the first component are therefore closed the remaining segment joints of the second component are each set ver in the direction of rotation.
  • the remaining segment joints of the first component each overlap with exactly one segment of the second component, and the remaining segment joints of the second component each overlap with exactly one segment of the first component.
  • the segments are preferably the same size, so they extend over the same angle (which is generally true); the offset of the remaining segment joints then preferably results from different segment numbers (which are in a non-integer ratio).
  • all segments of the first component are structurally identical to one another and / or all segments of the second component are structurally identical to one another.
  • the provision of structurally identical segments can, for example, help prevent assembly errors.
  • first and second segments of the first component could be angled to the abutting edges of the first and second segments of the second component and the remaining segment joints could be aligned parallel to one another.
  • the first and the second component can each surround a gas duct, for example a hot gas duct, of the turbomachine, in particular the turbofan engine, in a ring shape.
  • the two components can be axially adjacent and only partially overlap axially, ie the axial overlap area can correspond to only a part, for example 2% -30%, of the axial extent of the first and / or the second component.
  • the overlap area can be completely and continuously in the circumferential direction (without taking segment gaps into account).
  • the axial overlap area can also amount to the entire axial extent of the first and / or the second component or more than 80% thereof.
  • the first and second components are different housing shells.
  • the first component in a preferred embodiment is a guide vane ring and the second component is an outer air seal, in particular with an inlet coating and with a carrier for the inlet coating that surrounds the guide vane ring radially outward and / or partially axially with the Guide vane ring overlaps.
  • An application in the turbine area is generally preferred.
  • the invention also relates to a turbomachine with a module disclosed here.
  • the turbo machine can in particular be an aircraft engine such. B. a turbofan engine.
  • Figure 1 shows a turbo machine, namely a jacket current engine in one
  • FIG. 2 two components of a turbomachine in a schematic axial view
  • Figure 3 shows a section of the arrangement according to Figure 2 in a schematic
  • FIG. 4 shows an axial section through the arrangement according to FIG.
  • turbomachine 1 specifically a turbofan engine, in an axial section.
  • the flow machine 1 is functionally divided into compressor la, combustion chamber lb and turbine lc.
  • Both the compressor la and the turbine l c are each made up of several stages, each stage is composed of a guide and a subsequent rotor blade ring.
  • the rotor blade rings rotate around the longitudinal axis 2 of the turbo machine 1.
  • the air that is sucked in is compressed in the compressor la, and then burned in the downstream combustion chamber lb with the kerosene added.
  • the hot gas is expanded in the turbine 1c and thereby drives the rotor blade rings, which rotate about the longitudinal axis 2.
  • FIG. 2 shows a module 20 which has a first component 21 and a second component 22.
  • the first component 21 can in particular be a guide vane ring
  • the second component 22 is then an external air seal (OAS).
  • Both components 21, 22 are each segmented, that is to say each divided into several segments 21.1-21.4, 22.1-22.5.
  • FIG. 3 shows a detailed view of this revolving position 25, looking at it radially from the outside.
  • Axial direction 30, parallel to longitudinal axis 2, and direction of rotation 31 are shown for orientation.
  • FIG. 4 shows an axial section through the arrangement according to FIG. 3 (cf. the section line AA marked in FIG. 3).
  • the abutting edges 21.1.1, 21.2.1 of the segments 21.1, 21.2 of the first component 21 are angled to the axial direction 30 and form an angle 35 with the abutting edges 22.1.1, 22.2.1 of the segments 22.1, 22.2 of the second component 22. In the present example, this is around 90 °.
  • the abutting edges 21.1.1, 21.2.1, 22.1.1, 22.2.1 cross one another in such a way that each of the segments 21.1, 21.2 of the first component 21 touches both segments 22.1, 22.2 of the second component 22 in every thermal expansion state. Accordingly, as explained in detail in the introduction to the description, a reciprocal hooking can be prevented, that is, a hooking of the segment 21.1 with the segment 22.2 and the segment 22.1 with the segment 21.2.
  • the axial overlap 40 of the components 21, 22 can also be seen, the section according to FIG. 4 illustrates the radial offset 41. Looking at the two figures together, it can be seen that the first and the second component 21, 22 in the area of the axial overlap 40 have a contact surface 42 aneinan the. The joint edges 21.1.1, 21.2.1, 22.1.1, 22.2.1 which form the respective segment joint 23, 24 are also located in this contact surface 42.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un module (20) pour une turbomachine (1), comprenant deux composants (21, 22), qui s'étendent chacun de manière périphérique et qui sont segmentés, lesquels composants (21, 22) présentent un recouvrement axial (40) et ont un décalage radial (41) l'un par rapport à l'autre de telle sorte qu'ils entrent en contact l'un avec l'autre dans une zone de contact (42), et des joints de segment (23, 24) des deux composants (21, 22) coïncident à une position de rotation (25), un bord d'impact (21,1,1) du premier segment (21.1) du premier composant (21) avec des bords d'impact (22.1.1. 22.2.1) du premier et du second segment (22. 1, 22,2) du deuxième composant forme un angle (35).
PCT/DE2020/000175 2019-08-01 2020-07-29 Module pour une turbomachine WO2021018333A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE102019211524.1 2019-08-01
DE102019211524.1A DE102019211524A1 (de) 2019-08-01 2019-08-01 Modul für eine strömungsmaschine

Publications (1)

Publication Number Publication Date
WO2021018333A1 true WO2021018333A1 (fr) 2021-02-04

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ID=72086637

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/DE2020/000175 WO2021018333A1 (fr) 2019-08-01 2020-07-29 Module pour une turbomachine

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DE (1) DE102019211524A1 (fr)
WO (1) WO2021018333A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130022459A1 (en) * 2011-07-18 2013-01-24 General Electric Company Seals for reducing leakage in rotary machines
EP2857639A1 (fr) * 2013-10-01 2015-04-08 Siemens Aktiengesellschaft Anneau d'étanchéité
EP3375980A1 (fr) * 2017-03-13 2018-09-19 MTU Aero Engines GmbH Porte-joint pour une turbomachine

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP3968620B2 (ja) * 1999-02-05 2007-08-29 イーグル・エンジニアリング・エアロスペース株式会社 ブラシ型シール装置
US10125788B2 (en) * 2016-01-08 2018-11-13 General Electric Company Ceramic tile fan blade containment

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130022459A1 (en) * 2011-07-18 2013-01-24 General Electric Company Seals for reducing leakage in rotary machines
EP2857639A1 (fr) * 2013-10-01 2015-04-08 Siemens Aktiengesellschaft Anneau d'étanchéité
EP3375980A1 (fr) * 2017-03-13 2018-09-19 MTU Aero Engines GmbH Porte-joint pour une turbomachine

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DE102019211524A1 (de) 2021-02-04

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