EP3521562B1 - Schaufel einer strömungsmaschine - Google Patents

Schaufel einer strömungsmaschine Download PDF

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Publication number
EP3521562B1
EP3521562B1 EP19152152.5A EP19152152A EP3521562B1 EP 3521562 B1 EP3521562 B1 EP 3521562B1 EP 19152152 A EP19152152 A EP 19152152A EP 3521562 B1 EP3521562 B1 EP 3521562B1
Authority
EP
European Patent Office
Prior art keywords
rib
blade
ribs
sealing tip
shroud segment
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.)
Active
Application number
EP19152152.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP3521562A1 (de
Inventor
Martin Pernleitner
Klaus Wittig
Lutz Friedrich
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 EP3521562A1 publication Critical patent/EP3521562A1/de
Application granted granted Critical
Publication of EP3521562B1 publication Critical patent/EP3521562B1/de
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • F01D5/12—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
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow blades
    • 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
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/10—Manufacture by removing material
    • 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
    • F05D2230/00—Manufacture
    • F05D2230/20—Manufacture essentially without removing material
    • F05D2230/21—Manufacture essentially without removing material by casting
    • 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
    • F05D2250/00—Geometry
    • F05D2250/70—Shape
    • F05D2250/75—Shape given by its similarity to a letter, e.g. T-shaped
    • 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 present invention relates to a blade of a turbomachine according to claim.
  • Rotors of compressor stages and / or of turbine stages of turbo machines can be exposed to high forces, in particular centrifugal forces, at high speeds. These centrifugal forces can lead to deformation and even material damage to the rotors.
  • outer shrouds of high-speed turbine blades can be structurally reinforced. A possible reinforcement is an improved rigidity of the outer shroud by means of constructive measures.
  • the EP 2 402 559 A1 relates to a rotor blade, the outer shroud of which is provided with circumferential and several inner ribs for stiffening purposes.
  • the US 6,491,498 B1 relates to a rotor blade with an outer shroud that is stiffened by two circumferential ribs and one extending along the skeleton line.
  • a blade of a turbomachine in particular a gas turbine, is provided with a shroud segment and a blade profile, with one opposite one Shroud segment surface raised stiffening structure claimed.
  • the stiffening structure has at least three interconnected ribs.
  • the ribs can be referred to as stiffening ribs or webs.
  • a first end region of each of the at least three ribs is connected to an upstream sealing tip of the shroud segment, the end region relating to the longitudinal alignment or main axis of the ribs.
  • a second end region, which extends to the second, longitudinally opposite end of the Ribs related is connected to a downstream sealing tip of the shroud segment.
  • the blade according to the invention comprises a shroud segment for arrangement on a blade of a turbomachine with a stiffening structure that is raised with respect to a shroud segment surface.
  • the stiffening structure has at least three interconnected ribs. A first end region of the at least three ribs is connected to an upstream sealing tip of the shroud segment. A second end region, which relates to the second, opposite end of the ribs, is connected to a sealing tip of the shroud segment arranged downstream.
  • the angles between the direction of the axis of rotation of the blade and the longitudinal orientations of the ribs, viewed in the direction of flow through the turbomachine, are between zero degrees and eighty degrees.
  • the blade according to the invention is made in one piece, for example by means of a casting process or by means of a generative manufacturing process.
  • the blade according to the invention can be a compressor blade and / or a turbine blade of a gas turbine.
  • Exemplary embodiments according to the invention can have one or more of the features mentioned below in any combination, provided that one or the specific combination is not recognizable as obviously technically impossible for the person skilled in the art.
  • the subjects of the subclaims also each specify exemplary embodiments according to the invention.
  • a raised stiffening structure is in particular a structure made up of accumulations of material, such as ribs, webs or the like, which extend radially outward in the radial direction, starting from the shroud segment surface.
  • the stiffening structure can be made of the same material or a different material than the rest of the shroud, or parts of the rest of the shroud.
  • the three interconnected ribs of the shroud according to the invention form a Z-shaped rib structure.
  • a sealing tip can be referred to as a sealing fin.
  • a shroud or a shroud segment can be arranged on a blade tip.
  • One, two or more sealing tips on these shrouds or shroud segments can rub against a contact area of an inlet seal in a housing section of the turbomachine when the shroud or shroud segment rotates.
  • a sealing gap can form between the cover band and the housing, which gap minimizes the flow losses due to a backflow or a leakage flow.
  • the shroud segment can reduce the flow around the radially outer blade tip and thereby increase the efficiency of the turbomachine.
  • the shroud segments of adjacent or adjoining blades of a rotor form a continuous shroud.
  • the sealing tip arranged upstream is referred to below as the front sealing tip and the sealing tip arranged downstream is referred to as the rear sealing tip.
  • a first end portion of a first rib is connected to a first end portion of a second rib.
  • the two end sections connected to one another are arranged on the front sealing tip, in particular they are materially connected to the sealing tip.
  • a first end portion of a third rib is arranged offset in the circumferential direction, the offset arrangement relating to the connected end portions of the first and second ribs. This first end section of the third rib is arranged on the likewise front sealing tip, in particular connected to the sealing tip with a material fit.
  • the distance of the offset arrangement of the end section of the third rib with respect to the connected end sections of the first and second rib is in particular at least the width (in the circumferential direction) of the interconnected end sections of the first and second ribs arranged on the front sealing tip.
  • the angle between the direction of the axis of rotation of the blade and the longitudinal orientation of the first rib can be between 0 ° and 45 °
  • the angle between the direction of the axis of rotation of the blade and the longitudinal orientation of the third rib can be between 0 ° and 45 ° and / or the angle between the direction of the axis of rotation of the blade and the longitudinal orientation of the second rib can be between 30 ° and 80 °.
  • the skeleton line of the blade profile intersects the three ribs (in each case) at an angle between 30 ° and 90 °, in the radial viewing direction. It preferably cuts the second rib, preferably all three ribs, in each case at an angle between 45 ° and 90 °.
  • the skeleton line runs through the center of each circle, which is completely inscribed in the blade profile as a maximum circle at a specific axial position.
  • roots The respective arrangements of the end sections of the ribs on the sealing tips can be referred to as roots.
  • a second end section of the first rib is arranged on the rear sealing tip, in particular connected with a material fit to the sealing tip.
  • a second end portion of the second rib is connected to a second end portion of the third rib.
  • the rigidity of the shroud segment can advantageously be increased.
  • a first polygonal pocket is formed as a bottom surface between the side surfaces of the first and second ribs, the rear sealing tip and the shroud segment surface. Furthermore, a second polygonal pocket is formed between the second and third ribs, the front sealing tip and the shroud segment surface.
  • a pocket can be referred to as a recess, tub, bowl or the like.
  • a polygonal pocket is a pocket with multiple sides. The pockets have more than three side surfaces.
  • the side surfaces of the first polygonal pocket are essentially formed by the first rib, the second rib and the rear sealing tip.
  • the side surfaces of the second polygonal pocket are essentially formed by the second rib, the third rib and the front sealing tip. Both pockets can each have several side surfaces.
  • further side surfaces can be formed on the respective roots and / or on the transition areas between ribs and shroud segment surface.
  • the rigidity of the shroud segment can advantageously be increased.
  • the three ribs are essentially straight in their longitudinal alignment or in their main axes.
  • the end region of the third rib located at the front sealing tip is arranged on the connecting surface of the shroud segment to the closest shroud segment.
  • the end region of the first rib located at the rear sealing tip is arranged in the middle third, based on the length of the shroud segment in the circumferential direction.
  • the angle between the direction of the axis of rotation of the blade, i.e. the axial direction a, and the longitudinal directions of the first and third ribs, viewed in the flow direction of the turbomachine is between twenty degrees and seventy degrees, in particular between thirty degrees and fifty degrees , further in particular about forty-five degrees. In other embodiments the angle is between the directions the axis of rotation of the blade and the longitudinal directions of the first and third ribs are zero degrees or approximately zero degrees.
  • the ribs have a substantially radially constant height above the circumference.
  • the shroud segment is produced in one piece by means of a casting process, by means of a material-removing process, in particular by means of milling, or by means of a generative manufacturing process.
  • the shroud segment according to the invention advantageously enables high rigidity of the shroud or the outer band, in particular in the case of high-speed turbine blades.
  • One parameter in this context is the product AN 2 , where A is the ring area formed by the blades, in particular turbine blades, and further in particular by the last stage downstream. N corresponds to the speed of the blade in the application.
  • Large shroud overhangs can arise, particularly with a small number of blades or with very high AN 2.
  • the surface taper can be very large in the radial direction from the inside to the outside. In order that these shroud overhangs do not bend too much due to possible high centrifugal forces, ribs can be introduced into the shroud according to the invention. Furthermore, it is also advantageous that the increase in mass due to the stiffening structures designed as ribs should be as small as possible.
  • Fig. 1 shows a shroud segment 100 according to the invention with a stiffening structure and an airfoil 1 connected to the shroud segment 100 in a perspective view.
  • the stiffening structure has three interconnected ribs 3, 5, 7.
  • the ribs 3, 5, 7 extend in their longitudinal alignment or along their main axes from an upstream sealing tip 11, viewed in relation to a main flow direction 9 of the turbomachine, to a downstream sealing tip 13
  • Sealing tip 11 is referred to as the front sealing tip 11 and the sealing tip 13 arranged downstream is referred to as the rear sealing tip 13.
  • the front sealing tip 11 can also be referred to as the sealing tip front edge and the rear sealing tip 13 as the sealing tip rear edge.
  • the sealing tips 11, 13 can be referred to as sealing fins.
  • the ribs 3, 5, 7 are connected to a shroud segment surface 15.
  • the sealing tips 11, 13 can be used with a rotation of the shroud segment 100 with the blade 1 or with a rotation of an entire shroud rub with blades in a scraping area of an inlet seal in a housing section of the gas turbine.
  • a sealing gap can form between the cover band and the housing, which gap minimizes the flow losses due to a backflow or a leakage flow.
  • the shroud segment 100 can reduce the flow around the radially outer blade tip and thereby increase the efficiency of the turbomachine.
  • the shroud segments 100 of adjacent or adjoining blades of a rotor thereby form a continuous shroud.
  • the shroud segment 100 arranged at the radial end region of the airfoil 1 can in principle be used for damping blade vibrations, in particular in the case of gas turbine blades for rear, that is to say downstream, turbine stages.
  • the shrouds can advantageously have the shroud segments 100 according to the invention.
  • the Raised stiffening structures of the shroud segments 100 according to the invention can further contribute to reducing stress concentrations in the shroud.
  • the three interconnected ribs 3, 5, 7 are referred to below as the first rib 3, the second rib 5 and the third rib 7 for a simplified description.
  • the angle between the direction of the axis of rotation of the blade, which is referred to as the axial direction a and which depicts the skin flow direction 9, and the longitudinal orientations of the three ribs 3, 5, 7, viewed in the axial direction a, is approximately between thirty degrees in this exemplary embodiment and eighty degrees. This is done in Fig. 2 described in more detail.
  • a first polygon-shaped pocket 17 is formed, which can be referred to as a trough-shaped recess.
  • the first polygonal pocket 17 is arranged between the connecting areas of the first rib 3 and the second rib 5, the first rib 3 and the rear sealing tip 13 and between the second rib 5 and the rear sealing tip 13.
  • a second polygonal pocket 19 is formed between the second rib 5, the third rib 7 and the front sealing tip 11.
  • the second polygonal pocket 19 is arranged between the connecting areas of the second rib 5 and the third rib 7, the second rib 5 and the front sealing tip 11 and between the third rib 7 and the front sealing tip 11.
  • the sealing tips 11, 13 extend in their entire extent from below the shroud segment surface 15, i.e. in the area of the radially outer blade edge of the airfoil 1, to above the shroud segment surface 15.
  • the engagement area is an optional Inlet seal arranged in the housing area of the turbomachine.
  • the blade according to the invention comprises at least one shroud segment 100, a blade 1 and a blade root (in Fig. 1 not shown).
  • the blade can be manufactured as a one-piece cast component, by means of a material-removing method, in particular by means of milling, or by means of a generative manufacturing method.
  • Fig. 2 shows the shroud segment 100 according to the invention Fig. 1 in a plan view from the radial outside.
  • the first rib 3, the second rib 5 and the third rib 7 extend in their Longitudinal alignments, i.e. in the first main axis 17 of the first rib 3, in the second main axis 19 of the second rib 5 and in the third main axis 21 of the third rib 7, from the front sealing tip 11 to the rear sealing tip 13.
  • the three ribs 3, 5 , 7 are aligned essentially straight along their main axes 21, 23, 25.
  • the ribs 3, 5, 7 are connected to the sealing tips 11, 13 and, in this exemplary embodiment, to the shroud segment surface 15.
  • the raised stiffening structure designed as ribs 3, 5, 7 is manufactured in one piece with the shroud segment surface 15 and the sealing tips 11, 13, for example by means of a casting process or by means of a generative manufacturing process.
  • the in Fig. 2 The distance shown between on the one hand the upstream end regions of the first rib 3, the second rib 5 (which is connected to the first rib 3 in this end region) and the third rib 9 and on the other hand the front sealing tip 11 can be a connection of the ribs 3, 5, 7 indicate in the area of the shroud segment surface 15.
  • the downstream end areas of the ribs 3, 5, 7 in this view are connected directly to the rear sealing tip 11, which indicates a connection in the radially outer area of the sealing tip 13. This is also immediately in Fig. 1 recognizable.
  • the connection surface 27 can be referred to as a contact surface.
  • the connecting surface 27 is an essentially Z-shaped connecting surface 27.
  • a shroud with such Z-shaped connecting surfaces 27 can be referred to as a so-called Z-Shroud.
  • the already to Fig. 1 described polygonal pockets 17, 19 have several adjoining surfaces.
  • the surfaces are in particular side surfaces.
  • the pockets 17, 19 can have four, five, six or more side surfaces.
  • the side surfaces can be arranged, for example, at the junction of the first rib 3 and the second rib 5, at the junction of the second rib 5 and the third rib 7 and also at the junction of the ribs 3, 5, 7 with the sealing tips 11, 13. More as three side surfaces can advantageously increase the rigidity of the shroud segment 100 according to the invention.
  • the three angles W1, W2, W3 between the direction of the axis of rotation of the blade, i.e. the axial direction a, and the longitudinal orientations or main axes 21, 23, 25 of the ribs 3, 5, 7, each viewed in the flow direction 9, are between zero and eighty degrees.
  • the angle W1 between the axial direction a and the main axis 21 is approximately thirty degrees (30 °)
  • the angle W2 between the axial direction a and the main axis 23 is approximately sixty degrees (60 °)
  • the angle W3 between the Axial direction a and the main axis 25 approximately thirty degrees (30 °).
  • the end region of the first rib 3 located at the rear sealing tip 13 is arranged in the middle third L1, based on the length L of the shroud segment 100 in the circumferential direction u.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP19152152.5A 2018-01-29 2019-01-16 Schaufel einer strömungsmaschine Active EP3521562B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102018201265.2A DE102018201265A1 (de) 2018-01-29 2018-01-29 Deckbandsegment zur Anordnung an einer Schaufel einer Strömungsmaschine und Schaufel

Publications (2)

Publication Number Publication Date
EP3521562A1 EP3521562A1 (de) 2019-08-07
EP3521562B1 true EP3521562B1 (de) 2021-03-24

Family

ID=65033540

Family Applications (1)

Application Number Title Priority Date Filing Date
EP19152152.5A Active EP3521562B1 (de) 2018-01-29 2019-01-16 Schaufel einer strömungsmaschine

Country Status (4)

Country Link
US (1) US10914180B2 (es)
EP (1) EP3521562B1 (es)
DE (1) DE102018201265A1 (es)
ES (1) ES2866169T3 (es)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
PL3865660T3 (pl) 2020-02-11 2024-06-24 Mtu Aero Engines Gmbh Sposób obróbki łopatki i łopatka dla turbomaszyny

Family Cites Families (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5971710A (en) * 1997-10-17 1999-10-26 United Technologies Corporation Turbomachinery blade or vane with a permanent machining datum
US6491498B1 (en) 2001-10-04 2002-12-10 Power Systems Mfg, Llc. Turbine blade pocket shroud
DE10328310A1 (de) 2003-06-23 2005-01-13 Alstom Technology Ltd Verfahren zum Modifizieren der Kopplungsgeometrie bei Deckbandsegmenten von Turbinenlaufschaufeln
DE102009030566A1 (de) 2009-06-26 2010-12-30 Mtu Aero Engines Gmbh Deckbandsegment zur Anordnung an einer Schaufel
EP2402559B1 (en) * 2010-07-01 2018-11-07 MTU Aero Engines AG Turbine blade with tip shroud
EP2938832B1 (en) 2012-12-28 2019-02-06 United Technologies Corporation Shrouded turbine blade with cut corner
FR3001758B1 (fr) 2013-02-01 2016-07-15 Snecma Aube de rotor de turbomachine
US9683446B2 (en) 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
US9631500B2 (en) 2013-10-30 2017-04-25 General Electric Company Bucket assembly for use in a turbine engine
US9556741B2 (en) * 2014-02-13 2017-01-31 Pratt & Whitney Canada Corp Shrouded blade for a gas turbine engine
EP3006673A1 (en) 2014-10-07 2016-04-13 Siemens Aktiengesellschaft Method for and arrangement for measuring shrouded blade interlock wear
EP3056677B1 (de) 2015-02-12 2019-09-04 MTU Aero Engines GmbH Schaufel und Strömungsmaschine

Non-Patent Citations (1)

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Title
None *

Also Published As

Publication number Publication date
ES2866169T3 (es) 2021-10-19
DE102018201265A1 (de) 2019-08-01
EP3521562A1 (de) 2019-08-07
US20190234219A1 (en) 2019-08-01
US10914180B2 (en) 2021-02-09

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