CA2756914C - Dispositif d'installation de turbine - Google Patents

Dispositif d'installation de turbine Download PDF

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Publication number
CA2756914C
CA2756914C CA2756914A CA2756914A CA2756914C CA 2756914 C CA2756914 C CA 2756914C CA 2756914 A CA2756914 A CA 2756914A CA 2756914 A CA2756914 A CA 2756914A CA 2756914 C CA2756914 C CA 2756914C
Authority
CA
Canada
Prior art keywords
duct wall
bypass duct
engine
core portion
rods
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
CA2756914A
Other languages
English (en)
Other versions
CA2756914A1 (fr
Inventor
Jeffrey Bernard Heyerman
Bryan Olver
Stephen Caulfeild
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.)
Pratt and Whitney Canada Corp
Original Assignee
Pratt and Whitney Canada Corp
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 Pratt and Whitney Canada Corp filed Critical Pratt and Whitney Canada Corp
Priority to CA2756914A priority Critical patent/CA2756914C/fr
Publication of CA2756914A1 publication Critical patent/CA2756914A1/fr
Application granted granted Critical
Publication of CA2756914C publication Critical patent/CA2756914C/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/06—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front fan
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Une turbine à gaz comporte une structure de montage arrière comprenant un appareil de montage fixé à la paroi dun conduit de dérivation avec un dispositif de liaison de six tiges pour transférer des charges induites par inertie liées à la partie centrale, à partir dun boîtier intérieur de la partie centrale dans un court circuit à travers un passage dair en dérivation annulaire vers la paroi du conduit de dérivation.
CA2756914A 2011-11-04 2011-11-04 Dispositif d'installation de turbine Active CA2756914C (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CA2756914A CA2756914C (fr) 2011-11-04 2011-11-04 Dispositif d'installation de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CA2756914A CA2756914C (fr) 2011-11-04 2011-11-04 Dispositif d'installation de turbine

Publications (2)

Publication Number Publication Date
CA2756914A1 CA2756914A1 (fr) 2013-05-04
CA2756914C true CA2756914C (fr) 2019-01-22

Family

ID=48222491

Family Applications (1)

Application Number Title Priority Date Filing Date
CA2756914A Active CA2756914C (fr) 2011-11-04 2011-11-04 Dispositif d'installation de turbine

Country Status (1)

Country Link
CA (1) CA2756914C (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3010147B1 (fr) 2013-08-28 2015-08-21 Snecma Suspension isostatique d'un turboreacteur par double support arriere
GB201418396D0 (en) * 2014-10-17 2014-12-03 Rolls Royce Plc Gas turbine engine support structures
GB2640862A (en) * 2024-05-07 2025-11-12 Rolls Royce Plc Arrangement of components

Also Published As

Publication number Publication date
CA2756914A1 (fr) 2013-05-04

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