CH707767A8 - Housing with cooling unit for a gas turbine. - Google Patents

Housing with cooling unit for a gas turbine. Download PDF

Info

Publication number
CH707767A8
CH707767A8 CH00354/14A CH3542014A CH707767A8 CH 707767 A8 CH707767 A8 CH 707767A8 CH 00354/14 A CH00354/14 A CH 00354/14A CH 3542014 A CH3542014 A CH 3542014A CH 707767 A8 CH707767 A8 CH 707767A8
Authority
CH
Switzerland
Prior art keywords
turbine
gas turbine
wall
housing
cooling unit
Prior art date
Application number
CH00354/14A
Other languages
German (de)
Other versions
CH707767A2 (en
Inventor
Kenneth Black
Donald Earl Floyd
Original Assignee
Gen Electric
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 Gen Electric filed Critical Gen Electric
Publication of CH707767A2 publication Critical patent/CH707767A2/en
Publication of CH707767A8 publication Critical patent/CH707767A8/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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/14—Casings modified therefor
    • 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
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/20—Actively adjusting tip-clearance

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Die Erfindung betrifft eine innere Wand (100) für einen Turbinenabschnitt einer Gasturbine, die eine oder mehrere Befestigungsnuten (120) aufweist, von denen jede eine Fluidleitung (200) aufnimmt. Ein Temperatursteuerfluid wird durch die Fluidleitung (200) zirkuliert, um selektiv umgebende Bereiche der inneren Turbinenwand (110) zu erwärmen oder zu kühlen, um dadurch die thermische Ausdehnung dieser Bereiche der inneren Turbinenwand (110) zu steuern. Dadurch ist es möglich, einen Freiraum zwischen den Spitzen von rotierenden Turbinenschaufeln und den umgebenden Deckbändern der Turbine selektiv zu steuern.The invention relates to an inner wall (100) for a turbine section of a gas turbine having one or more mounting grooves (120), each receiving a fluid conduit (200). A temperature control fluid is circulated through the fluid line (200) to selectively heat or cool portions of the inner turbine wall (110) surrounding it to thereby control the thermal expansion of those portions of the inner turbine wall (110). This makes it possible to selectively control a clearance between the tips of rotating turbine blades and the surrounding shrouds of the turbine.

CH00354/14A 2013-03-14 2014-03-10 Housing with cooling unit for a gas turbine. CH707767A8 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/828,081 US20140271154A1 (en) 2013-03-14 2013-03-14 Casing for turbine engine having a cooling unit

Publications (2)

Publication Number Publication Date
CH707767A2 CH707767A2 (en) 2014-09-15
CH707767A8 true CH707767A8 (en) 2015-01-15

Family

ID=51419070

Family Applications (1)

Application Number Title Priority Date Filing Date
CH00354/14A CH707767A8 (en) 2013-03-14 2014-03-10 Housing with cooling unit for a gas turbine.

Country Status (5)

Country Link
US (1) US20140271154A1 (en)
JP (1) JP2014177937A (en)
CN (1) CN204283516U (en)
CH (1) CH707767A8 (en)
DE (1) DE102014103009A1 (en)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3023600B1 (en) * 2014-11-24 2018-01-03 Ansaldo Energia IP UK Limited Engine casing element
US9915153B2 (en) * 2015-05-11 2018-03-13 General Electric Company Turbine shroud segment assembly with expansion joints
GB201521937D0 (en) * 2015-12-14 2016-01-27 Rolls Royce Plc Gas turbine engine turbine cooling system
EP3342991B1 (en) * 2016-12-30 2020-10-14 Ansaldo Energia IP UK Limited Baffles for cooling in a gas turbine
US11466700B2 (en) * 2017-02-28 2022-10-11 Unison Industries, Llc Fan casing and mount bracket for oil cooler
US10533747B2 (en) * 2017-03-30 2020-01-14 General Electric Company Additively manufactured mechanical fastener with cooling fluid passageways
FR3098238B1 (en) * 2019-07-04 2021-06-18 Safran Aircraft Engines improved aircraft turbine ring cooling system

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4513567A (en) * 1981-11-02 1985-04-30 United Technologies Corporation Gas turbine engine active clearance control
FR2540939A1 (en) * 1983-02-10 1984-08-17 Snecma SEALING RING FOR A TURBINE ROTOR OF A TURBOMACHINE AND TURBOMACHINE INSTALLATION PROVIDED WITH SUCH RINGS
US5116199A (en) * 1990-12-20 1992-05-26 General Electric Company Blade tip clearance control apparatus using shroud segment annular support ring thermal expansion
US5281085A (en) * 1990-12-21 1994-01-25 General Electric Company Clearance control system for separately expanding or contracting individual portions of an annular shroud
US5273396A (en) * 1992-06-22 1993-12-28 General Electric Company Arrangement for defining improved cooling airflow supply path through clearance control ring and shroud
FR2766517B1 (en) * 1997-07-24 1999-09-03 Snecma DEVICE FOR VENTILATION OF A TURBOMACHINE RING
US6702550B2 (en) * 2002-01-16 2004-03-09 General Electric Company Turbine shroud segment and shroud assembly
FR2852053B1 (en) * 2003-03-06 2007-12-28 Snecma Moteurs HIGH PRESSURE TURBINE FOR TURBOMACHINE
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly
US7165937B2 (en) * 2004-12-06 2007-01-23 General Electric Company Methods and apparatus for maintaining rotor assembly tip clearances
US20070009349A1 (en) * 2005-07-11 2007-01-11 General Electric Company Impingement box for gas turbine shroud
FR2907841B1 (en) * 2006-10-30 2011-04-15 Snecma TURBINE MACHINE RING SECTOR
GB0703827D0 (en) * 2007-02-28 2007-04-11 Rolls Royce Plc Rotor seal segment
US20090053042A1 (en) * 2007-08-22 2009-02-26 General Electric Company Method and apparatus for clearance control of turbine blade tip

Also Published As

Publication number Publication date
CN204283516U (en) 2015-04-22
US20140271154A1 (en) 2014-09-18
JP2014177937A (en) 2014-09-25
DE102014103009A1 (en) 2014-09-18
CH707767A2 (en) 2014-09-15

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PK Correction

Free format text: BERICHTIGUNG ERFINDER

PK Correction

Free format text: ERFINDER BERICHTIGT.

NV New agent

Representative=s name: GENERAL ELECTRIC TECHNOLOGY GMBH GLOBAL PATENT, CH

AZW Rejection (application)