PL416301A1 - Turbine engine shrouding bandage unit - Google Patents

Turbine engine shrouding bandage unit

Info

Publication number
PL416301A1
PL416301A1 PL416301A PL41630116A PL416301A1 PL 416301 A1 PL416301 A1 PL 416301A1 PL 416301 A PL416301 A PL 416301A PL 41630116 A PL41630116 A PL 41630116A PL 416301 A1 PL416301 A1 PL 416301A1
Authority
PL
Poland
Prior art keywords
bandage
elements
turbine engine
adjacent
lock
Prior art date
Application number
PL416301A
Other languages
Polish (pl)
Inventor
Marek Szrajer
Paweł Lopata
Original Assignee
General Electric Company
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 General Electric Company filed Critical General Electric Company
Priority to PL416301A priority Critical patent/PL416301A1/en
Priority to CA2958106A priority patent/CA2958106A1/en
Priority to JP2017026516A priority patent/JP2017198190A/en
Priority to EP17156817.3A priority patent/EP3225794A1/en
Priority to US15/441,597 priority patent/US20170306768A1/en
Priority to CN201710113770.0A priority patent/CN107131005A/en
Publication of PL416301A1 publication Critical patent/PL416301A1/en

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
    • 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
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using 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
    • 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
    • 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
    • F05D2240/12—Fluid guiding means, e.g. vanes
    • 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
    • F05D2240/80—Platforms for stationary or moving blades
    • 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
    • F05D2250/30—Arrangement of components
    • F05D2250/32—Arrangement of components according to their shape
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

[0003] W jednym aspekcie, rozwiązania odnoszące się do silnika turbinowego zawierającego wirnik posiadający wiele promieniowo ułożonych płatów rozłożonych na obwodzie wokół wirnika, z płatami zakończonymi końcówką, i zespołem bandaża (100) otaczającym płaty i obejmującego elementy bandaża mocowane do każdej końcówki i posiadające przeciwległe promieniowo zakończenia z pierwszymi i drugimi elementami zamków, w których pierwszy element zamka pierwszego elementu bandaża współpracuje z drugim elementem zamka obwodowe przyległym, w celu stworzenia wielu zamków pomiędzy przyległymi elementami bandaża na obwodzie płatów. [0004] W kolejnym aspekcie, rozwiązania odnoszą się do blokującego się zespołu bandaża dla silnika turbinowego zawierającego wiele promieniowo ułożonych, obwodowo rozmieszczonych płatów zakończonych elementami bandaża i posiadających przeciwległe strony promieniowe z pierwszymi i drugimi elementami zamykającymi, które zatrzaskują się tworząc zamki pomiędzy obwodowo przyległymi płatami. [0005] W jeszcze jednym aspekcie, rozwiązania odnoszą się do sposobu formowania bandaża wokół wielu obracających się łopatek w silnikach turbinowych polegającego na formowaniu zamka pomiędzy obwodowo przyległymi końcówkami łopatek i wstępnego obciążania zamków.[0003] In one aspect, solutions relating to a turbine engine comprising a rotor having a plurality of radially arranged lobes distributed circumferentially around the rotor, with lobes ending in a tip, and a bandage assembly (100) surrounding the lobes and including bandage elements attached to each end and having opposite radially ends with first and second lock elements, in which the first lock element of the first bandage element cooperates with the second adjacent lock element, to create multiple locks between adjacent bandage elements on the periphery of the panels. [0004] In a further aspect, the solutions relate to a locking bandage assembly for a turbine engine comprising a plurality of radially arranged, circumferentially spaced panels ending with bandage elements and having opposite radial sides with the first and second closing elements that latch to form locks between the peripherally adjacent panels . [0005] In yet another aspect, the solutions relate to a method of forming a bandage around a plurality of rotating blades in turbine engines consisting in forming a lock between the circumferentially adjacent blade tips and preloading the locks.

PL416301A 2016-02-29 2016-02-29 Turbine engine shrouding bandage unit PL416301A1 (en)

Priority Applications (6)

Application Number Priority Date Filing Date Title
PL416301A PL416301A1 (en) 2016-02-29 2016-02-29 Turbine engine shrouding bandage unit
CA2958106A CA2958106A1 (en) 2016-02-29 2017-02-16 Turbine engine shroud assembly
JP2017026516A JP2017198190A (en) 2016-02-29 2017-02-16 Turbine engine shroud assembly
EP17156817.3A EP3225794A1 (en) 2016-02-29 2017-02-20 Turbine engine shroud assembly
US15/441,597 US20170306768A1 (en) 2016-02-29 2017-02-24 Turbine engine shroud assembly
CN201710113770.0A CN107131005A (en) 2016-02-29 2017-02-28 Turbine engine shroud component

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PL416301A PL416301A1 (en) 2016-02-29 2016-02-29 Turbine engine shrouding bandage unit

Publications (1)

Publication Number Publication Date
PL416301A1 true PL416301A1 (en) 2017-09-11

Family

ID=58094284

Family Applications (1)

Application Number Title Priority Date Filing Date
PL416301A PL416301A1 (en) 2016-02-29 2016-02-29 Turbine engine shrouding bandage unit

Country Status (6)

Country Link
US (1) US20170306768A1 (en)
EP (1) EP3225794A1 (en)
JP (1) JP2017198190A (en)
CN (1) CN107131005A (en)
CA (1) CA2958106A1 (en)
PL (1) PL416301A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10738634B2 (en) 2018-07-19 2020-08-11 Raytheon Technologies Corporation Contact coupled singlets
CN114174636B (en) * 2019-06-28 2024-08-23 西门子能源全球两合公司 Outlet guide vane assembly in a gas turbine engine
FR3098746B1 (en) * 2019-07-17 2021-07-30 Safran Aircraft Engines TOOLS AND METHOD FOR DISMANTLING AND MOVING A TURBINE CASE OF THE TRV TYPE FROM AN AIRCRAFT TURBOMACHINE
US11208903B1 (en) 2020-11-20 2021-12-28 Solar Turbines Incorporated Stiffness coupling and vibration damping for turbine blade shroud
US11655719B2 (en) * 2021-04-16 2023-05-23 General Electric Company Airfoil assembly
JP2023119098A (en) * 2022-02-16 2023-08-28 三菱重工航空エンジン株式会社 turbine
FR3137121B1 (en) * 2022-06-22 2024-06-21 Safran Aircraft Engines Bladed assembly with inter-platform connection by interposed rolling element
CN117869016B (en) * 2024-03-12 2024-05-17 中国航发四川燃气涡轮研究院 Cooling unit for reducing heat conduction of turbine outer ring and analysis method thereof

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20080145227A1 (en) * 2006-12-19 2008-06-19 Mark Stefan Maier Methods and apparatus for load transfer in rotor assemblies
US8371816B2 (en) * 2009-07-31 2013-02-12 General Electric Company Rotor blades for turbine engines
US20120051930A1 (en) * 2010-08-31 2012-03-01 General Electric Company Shrouded turbine blade with contoured platform and axial dovetail
US8684674B2 (en) * 2010-10-29 2014-04-01 General Electric Company Anti-rotation shroud for turbine engines
US9163519B2 (en) * 2011-07-28 2015-10-20 General Electric Company Cap for ceramic blade tip shroud
US8894368B2 (en) * 2012-01-04 2014-11-25 General Electric Company Device and method for aligning tip shrouds
EP2666969B1 (en) * 2012-05-21 2017-04-19 General Electric Technology GmbH Turbine diaphragm construction

Also Published As

Publication number Publication date
EP3225794A1 (en) 2017-10-04
CN107131005A (en) 2017-09-05
JP2017198190A (en) 2017-11-02
CA2958106A1 (en) 2017-08-29
US20170306768A1 (en) 2017-10-26

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