EP4183982A1 - Pale pour une turbomachine - Google Patents

Pale pour une turbomachine Download PDF

Info

Publication number
EP4183982A1
EP4183982A1 EP22202319.4A EP22202319A EP4183982A1 EP 4183982 A1 EP4183982 A1 EP 4183982A1 EP 22202319 A EP22202319 A EP 22202319A EP 4183982 A1 EP4183982 A1 EP 4183982A1
Authority
EP
European Patent Office
Prior art keywords
blade
airfoil
tip
squealer tip
squealer
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.)
Pending
Application number
EP22202319.4A
Other languages
German (de)
English (en)
Inventor
Axel Stettner
Ulf Koellmann
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
Publication of EP4183982A1 publication Critical patent/EP4183982A1/fr
Pending legal-status Critical Current

Links

Images

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
    • F01D5/14—Form or construction
    • F01D5/20—Specially-shaped blade tips to seal space between tips and stator
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade
    • 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
    • F05D2260/00—Function
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction

Definitions

  • the invention relates to a blade for a turbomachine, having a leading edge and a trailing edge, which are connected to one another by a suction side and a pressure side and which extends curved in at least one area from a blade root to a blade tip. Furthermore, the invention relates to a compressor with such a blade leaf and a turbomachine.
  • a blade profile, an inclination or bending of the blade in the circumferential direction or a twisting of the blade can be used to reduce various types of flow losses when designing a three-dimensional blade.
  • blade tips of blade leaves in turbomachines for example rotor blades in aircraft engines, are regularly exposed to oscillating stresses. For example, these oscillating stresses can cause cracks in either a tip side armor and/or the airfoil body.
  • Such blade tips referred to as “squealer tips”, are known in many designs and can, for example, be designed on the pressure side or on the suction side.
  • a blade blade for a turbomachine which has a leading edge and a trailing edge, which are connected to one another by a suction side and a pressure side and which curves in at least one area from a blade blade root to a blade tip extends.
  • the blade tip has a squealer tip, which along a centroid at the airfoil tip, the centrifugal curve passing through the centrifugal axes of the airfoil.
  • a curved region of an airfoil may, for example, have a curvature, bend or inclination of a pressure side or a wall of the pressure side or a suction side or a wall of the suction side in a longitudinal and/or transverse extent.
  • a curvature can be based on a torsion or torsion of the airfoil about one of its axes and/or an in particular continuous change in cross-sectional profiles of the airfoil over its height.
  • a profile thickness of the airfoil can change while the chord length remains the same, cross-sectional profiles spaced apart from one another can be twisted relative to one another, or an edge angle has a change over the airfoil height.
  • a squealer tip is in particular a cross-sectionally tapered area of the blade tip, which can be formed, for example, by a suction-side tapering and/or a pressure-side tapering of the blade blade tip. Such a narrowing can be created in particular by removing material or by constriction in the region of the blade tip, with a region of the blade tip facing away therefrom remaining unchanged.
  • the squealer tip has a height in the axial direction of the airfoil, a longitudinal extent between the leading edge and the trailing edge of the airfoil, and a width between a suction-side flank and a pressure-side flank of the squealer tip.
  • the cross-section in relation to the height and the width of the squealer tip or the size(s) of the respective taper(s) are determined from the geometry and the requirements placed on the airfoil, in particular with regard to vibration stresses that occur during operation.
  • the design of a squealer tip with regard to its cross section is not the focus of the present invention and is therefore only discussed in passing.
  • a suction-side taper in at least one area of a longitudinal extension of the squealer tip, i.e. along the blade tip, a suction-side taper can be provided in the blade, with a pressure side wall of the blade forming the pressure-side flank of the squealer tip.
  • a pressure-side taper in the Airfoil may be provided, with a suction side wall of the airfoil forming the suction-side edge of the squealer tip.
  • a taper can be provided on both sides thereof, whereby both flanks of the squealer tip, at least in a section facing the squealer tip front side, are offset inwards in relation to the blade wall walls are.
  • the squealer tip face forms the outermost blade tip.
  • One or both flanks of the squealer tip can have a rounding, in particular in the form of a concave surface, in particular a radius, in a section adjoining one of the walls of the airfoil, as a result of which a mechanically stable structure of the squealer tip can be created.
  • the gravity curve runs on the front side of the airfoil tip through the gravity axes of cross-sectional areas of the airfoil that are perpendicular to the profile centerline.
  • a centroid is in particular the neutral fiber or the geometric central axis of such a cross-sectional area.
  • the airfoil centerline is the line connecting the centers of circles inscribed in an airfoil tip profile/airfoil section profile and is equidistant from the suction and pressure sides at each point.
  • the gravity curve extends in particular between the leading edge and the trailing edge of the blade tip and can be offset in an area facing the leading edge with respect to the profile center line towards the pressure side and/or in an area facing the trailing edge with respect to the profile center line towards the suction side.
  • vibration stresses at the blade tip can be reduced, as a result of which a risk of cracking in the area of the blade blade tip can be reduced and the vibration stress behavior of the blade blade can be improved.
  • the squealer tip is arranged on both sides of the gravity curve.
  • the squealer tip is designed, in particular over its entire height, in such a way that a centroid of the blade blade runs at at least one position of the centrifugal curve within a cross section of the squealer tip.
  • an embodiment of the squealer tip in which a flank is formed by a side wall of the blade leaf can be used to arrange the squealer tip on both sides of the gravity curve.
  • the squealer tip is thus arranged at least essentially centered around neutral fibers of the airfoil, as a result of which a reduction in vibration stress at the airfoil tip is made possible.
  • the squealer tip is arranged at least essentially symmetrically around the gravity curve, in particular in at least one area of its longitudinal extension.
  • the flanks of the squealer tip in particular at least in a region of its longitudinal extent, have an essentially symmetrical or symmetrical shape with respect to its center plane.
  • the flanks of the squealer tip can be designed parallel to one another over its height, in particular in at least one section, can be equally spaced in relation to a central axis of the squealer tip and/or a radius or a bevel in the transition from the blade blade cross section to the squealer Tip cross-section to be essentially the same.
  • the squealer tip is continuous, that is to say without interruption.
  • the squealer tip is designed to be particularly uniform or even invariant in its longitudinal extent between the front edge and the rear edge of the airfoil with respect to a width and/or height.
  • a cross-sectional width on the end face of the squealer tip can be designed to be uniform or even invariant. In this way, an improved sealing of the radial gap in the blade tip area can be achieved.
  • a height, a width and/or a flank geometry of the squealer tip can be variable over its course along the gravity curve in order to enable flexible adaptation to blade geometries and/or stress requirements.
  • a cross section of the squealer tip is smaller than a cross section of the airfoil tip.
  • a height of the squealer tip be greater than its width
  • the width of the squealer tip be greater than its height
  • the height and width of the squealer tip can be made substantially the same. Due to the reduction in cross section provided by the squealer tip, oscillating stresses in the blade tip area can be reduced, thereby enabling the blades to be able to withstand higher loads.
  • the invention also relates to an airfoil arrangement for a turbomachine, which has at least one airfoil described herein.
  • a blade arrangement comprises a rotor disk and a plurality of blade blades arranged radially thereon.
  • the blade blades are connected to the rotor disk in a form-fitting manner, or the blade blade arrangement has a plurality of blade blades which are integrally connected to the rotor disk in a materially bonded manner (blisk).
  • blisk materially bonded manner
  • the invention also relates to a compressor for a turbomachine with at least one blade blade configured as described herein and/or at least one blade blade arrangement described herein.
  • the compressor can be designed as a low-pressure compressor or a high-pressure compressor.
  • the invention also relates to a turbomachine with at least one blade leaf described herein and/or at least one blade leaf arrangement described herein.
  • the blades of several, preferably all, compressor or turbine stages are designed in a manner according to the invention.
  • a method for producing an airfoil for a turbomachine is proposed.
  • the centroids of the airfoil are determined as a function of a blade geometry.
  • a gravity curve at the blade tip is determined as a function of the gravity axes.
  • an arrangement of the squealer tip is determined as a function of the gravity curve determined, and in step d) the airfoil with the squealer tip is produced in accordance with the arrangement determined in step c).
  • a centroid or the neutral axis of a cross-sectional area of the blade that is perpendicular to the profile center line of the blade is determined. Based on a large number of centroids determined in this way in particular, a centroid curve can be determined in particular on the end face of the blade tip.
  • a course of the squealer tip at the blade tip, and in particular using further design criteria, for example its height, width and a flank geometry of the squealer tip can be determined on the basis of the determined gravity curve.
  • specifications regarding the placement and configuration of tapers or abrasions, in particular along or offset from the gravity curve, can be determined.
  • material may be removed from the blade tip to provide the squealer tip.
  • a use of an airfoil described herein in an airfoil arrangement and/or a compressor and/or a turbomachine is also the subject of the present disclosure.
  • the proposed design of the squealer tip can be used for all blade blades in a turbomachine that are exposed to oscillating stresses, in particular for turbine blade blades and also for cantilevered stators of the turbomachine.
  • the disclosure of the airfoil, airfoil assembly, compressor, and turbomachine described herein also applies to a corresponding method for designing or manufacturing an airfoil, and vice versa.
  • the characteristics and advantages of the various described above or below Exemplary aspects and exemplary embodiments can be combined unless explicitly stated otherwise.
  • FIG. 1 shows an exemplary embodiment of a blade 10 for a turbomachine in a schematic representation.
  • the airfoil has a leading edge 11 and a trailing edge 12 which are connected by a suction side 13 and a pressure side 14 .
  • the blade 10 extends curved in at least one area from a blade root (not shown) to a blade tip 21. Such a curvature is indicated schematically by a geometric profile section change 15.
  • the blade tip 21 has a substantially continuously formed squealer tip 22, which is arranged along a gravity curve on the blade tip 21, the gravity curve running through the centroids of the blade 10 (cf. 2 ).
  • the squealer tip 22 has a cross section, in particular orthogonal to the profile center line, which is smaller than such a cross section of the blade tip 21.
  • FIG. 12 shows a schematic representation of the airfoil tip 21 of the airfoil 10.
  • FIG 1 The airfoil 10 extends between an upstream leading edge 11 and a trailing edge 12.
  • the airfoil 10 has a suction side 13 and an opposite pressure side 14.
  • a profile centerline 16 is equidistant at each location from the suction side 13 and pressure side 14 of the airfoil 10 profile.
  • a centroid curve K of blade 10 runs at blade tip 21 through centroids of cross-sectional areas Q of blade 10 perpendicular to profile center line 16.
  • Figures 3a to 3c 12 each show a schematic representation of three airfoil cross-sections of the exemplary curved airfoil 10 2 .
  • the airfoil 10 has the squealer tip 22 at its airfoil tip 21 with a suction-side flank 23 and a pressure-side flank 24 .
  • FIG. 12 shows a schematic representation of the exemplary section AA of FIG 2 at a first centroid S A in a first region of the airfoil 10.
  • the squealer tip 22 has a height H, starting from an in particular unchanged blade cross-section up to the front end of the squealer tip 22 .
  • the squealer tip 22 has a width B, which is delimited by the suction-side flank 23 and the pressure-side flank 24 and is arranged in particular in an end region of the squealer tip 22, in which the suction-side flank 23 and the pressure-side flank 24 are at least Are formed substantially parallel to each other.
  • the squealer tip 22 is arranged on both sides of the centroid S A or the centroid K, with a suction-side taper 33 being arranged on the blade tip 21 of the blade 10 in order to form the suction-side flank 23 of the squealer tip 22 .
  • the pressure-side wall 14 of the airfoil 10 forms the pressure-side flank 24 of the squealer tip 22 .
  • the squealer tip 22 can be configured in this way in particular in a region facing the front edge 11 and/or at a distance from a turning point of the gravity curve K.
  • FIG. 12 shows a schematic representation of the exemplary section BB from FIG 2 on a second centroid axis S B in a second region of the airfoil 10.
  • the squealer tip 22 is arranged essentially symmetrically about the second centroid axis S B or about the centroid curve K.
  • the blade tip 21 has a taper 33, 34 on both the suction side and the pressure side, as a result of which the flanks 23, 24 of the squealer tip 22 are arranged offset inwards relative to a blade blade cross section.
  • FIG. 12 shows a schematic representation of the exemplary section CC of FIG 2 at a third centroid S C in a third region of the airfoil 10.
  • the squealer tip 22 is also arranged on both sides of the centroid S C or the gravity curve K, with a pressure-side taper 34 being arranged at the airfoil tip 21 of the airfoil 10 in order to pressure-side flank 24 of the squealer tip 22 to form.
  • the suction side wall 13 of the airfoil 10 forms the suction-side flank 23 of the squealer tip 22 .
  • the squealer tip 22 can be configured in this way, in particular, in a region facing the trailing edge 12 and/or at a distance from a turning point of the gravity curve K.
  • FIG. 12 shows a schematic representation of a flowchart of an exemplary method 100 for designing or manufacturing an airfoil 10 for a turbomachine.
  • centroids S of the airfoil 10 are determined based on a blade geometry.
  • a gravity curve K at the blade tip 21 is determined as a function of the gravity axes S.
  • an arrangement of a squealer tip 22 is determined as a function of the determined gravity curve K, and in a step 104 the airfoil 10 is produced with a squealer tip 22 according to the arrangement determined in step 103.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP22202319.4A 2021-11-23 2022-10-18 Pale pour une turbomachine Pending EP4183982A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102021130682.5A DE102021130682A1 (de) 2021-11-23 2021-11-23 Schaufelblatt für eine Strömungsmaschine

Publications (1)

Publication Number Publication Date
EP4183982A1 true EP4183982A1 (fr) 2023-05-24

Family

ID=83903092

Family Applications (1)

Application Number Title Priority Date Filing Date
EP22202319.4A Pending EP4183982A1 (fr) 2021-11-23 2022-10-18 Pale pour une turbomachine

Country Status (3)

Country Link
US (1) US11697995B2 (fr)
EP (1) EP4183982A1 (fr)
DE (1) DE102021130682A1 (fr)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120269638A1 (en) * 2011-04-20 2012-10-25 General Electric Company Compressor having blade tip features
US9399918B2 (en) * 2012-08-09 2016-07-26 Mtu Aero Engines Gmbh Blade for a continuous-flow machine and a continuous-flow machine
US20180245469A1 (en) * 2017-02-27 2018-08-30 Rolls-Royce Corporation Tip Structure for a Turbine Blade with Pressure Side and Suction Side Rails

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2623569A1 (fr) 1987-11-19 1989-05-26 Snecma Aube de compresseur a lechettes d'extremite dissymetriques
EP1624192A1 (fr) * 2004-08-06 2006-02-08 Siemens Aktiengesellschaft Aube de rouet pour compresseur axial
FR2891594A1 (fr) 2005-09-30 2007-04-06 Snecma Sa Aube de compresseur a sommet chanfreine
WO2013102135A2 (fr) * 2011-12-29 2013-07-04 Rolls-Royce North American Technologies Inc. Moteur à turbine à gaz et aube de turbine
EP3421724A1 (fr) 2017-06-26 2019-01-02 Siemens Aktiengesellschaft Surface portante de compresseur
EP3477059A1 (fr) * 2017-10-26 2019-05-01 Siemens Aktiengesellschaft Surface portante de compresseur
EP3561226A1 (fr) * 2018-04-24 2019-10-30 Siemens Aktiengesellschaft Surface portante de compresseur

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20120269638A1 (en) * 2011-04-20 2012-10-25 General Electric Company Compressor having blade tip features
US9399918B2 (en) * 2012-08-09 2016-07-26 Mtu Aero Engines Gmbh Blade for a continuous-flow machine and a continuous-flow machine
US20180245469A1 (en) * 2017-02-27 2018-08-30 Rolls-Royce Corporation Tip Structure for a Turbine Blade with Pressure Side and Suction Side Rails

Also Published As

Publication number Publication date
US20230160309A1 (en) 2023-05-25
DE102021130682A1 (de) 2023-05-25
US11697995B2 (en) 2023-07-11

Similar Documents

Publication Publication Date Title
DE3045224C2 (fr)
EP1953344B1 (fr) Aube de turbine
EP2696031B1 (fr) Aube pour une turbomachine et turbomachine correspondante
EP3176370B1 (fr) Ensemble d'aubes directrices pour turbomachine
EP3711945B1 (fr) Aube et rotor pour une turbomachine et turbomachine
EP2376746B1 (fr) Plateforme d'extrémité d' aube
DE102015219530A1 (de) Schaufel für eine Strömungsmaschine, Turbofantriebwerk und ein Verfahren zur Herstellung einer Schaufel
DE102008019332A1 (de) Verfahren zum Fräsen von Blisks
EP2106876A1 (fr) Tubes pour un dispositif d'observation
EP1439281A2 (fr) Aube de turbine à gaz
EP1759090A1 (fr) Aube comportant une zone de transition
EP1529962A2 (fr) Aube rotorique pour compresseur
EP1413712A1 (fr) Virole pour une turbine avec joint d'extrémité
DE102016112521A1 (de) Laufrad für einen Abgasturbolader, Abgasturbolader und Verfahren zum Auswuchten eines Laufzeugs für einen Abgasturbolader
EP1624192A1 (fr) Aube de rouet pour compresseur axial
EP3428402B1 (fr) Segment d'aube directrice à joint de décharge courbé
EP4183982A1 (fr) Pale pour une turbomachine
EP2090751A1 (fr) Aube pour turbomachine
EP2730745A1 (fr) Agencement d'aubes pour une turbomachine
EP3623576B1 (fr) Aube de turbine à gaz
EP3521562B1 (fr) Aube d'une turbomachine
EP2650475B1 (fr) Pale pour une turbomachine, agencement d'aubes ainsi que la turbomachine
DE102004004014A1 (de) Leitschaufel für eine Turbomaschine
EP4306770A1 (fr) Aube mobile pour agencement d'aubes mobiles d'une turbomachine et agencement d'aubes mobiles
EP4148284A1 (fr) Pale d'aube pour un compresseur d'une turbomachine

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION HAS BEEN PUBLISHED

AK Designated contracting states

Kind code of ref document: A1

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC ME MK MT NL NO PL PT RO RS SE SI SK SM TR

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: REQUEST FOR EXAMINATION WAS MADE

17P Request for examination filed

Effective date: 20231124

RBV Designated contracting states (corrected)

Designated state(s): AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC ME MK MT NL NO PL PT RO RS SE SI SK SM TR