ES257350A1 - Improvements in or relating to gas turbine engines - Google Patents

Improvements in or relating to gas turbine engines

Info

Publication number
ES257350A1
ES257350A1 ES0257350A ES257350A ES257350A1 ES 257350 A1 ES257350 A1 ES 257350A1 ES 0257350 A ES0257350 A ES 0257350A ES 257350 A ES257350 A ES 257350A ES 257350 A1 ES257350 A1 ES 257350A1
Authority
ES
Spain
Prior art keywords
guide vanes
movement
relating
gas turbine
link system
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.)
Expired
Application number
ES0257350A
Other languages
Spanish (es)
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Publication of ES257350A1 publication Critical patent/ES257350A1/en
Expired legal-status Critical Current

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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Transmission Devices (AREA)

Abstract

Gas turbomotor having: a compressor or turbine fitted with pivot-mounted guide vanes or steering vanes; a blade actuating device arranged inside the guide vanes, the movement of said device giving rise to a pivoting movement of the guide vanes; means disposed outside the motor to effect movement of the vane drive device; and an articulated link system, spaced from said blades and connecting the external means with the blade drive device, said link system being arranged so as not to cause any, or essentially no, obstruction to the passage of fluid through the engine. (Machine-translation by Google Translate, not legally binding)
ES0257350A 1959-04-30 1960-04-13 Improvements in or relating to gas turbine engines Expired ES257350A1 (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1478059A GB876504A (en) 1959-04-30 1959-04-30 Improvements in or relating to gas turbine engines

Publications (1)

Publication Number Publication Date
ES257350A1 true ES257350A1 (en) 1960-06-16

Family

ID=10047357

Family Applications (1)

Application Number Title Priority Date Filing Date
ES0257350A Expired ES257350A1 (en) 1959-04-30 1960-04-13 Improvements in or relating to gas turbine engines

Country Status (2)

Country Link
ES (1) ES257350A1 (en)
GB (1) GB876504A (en)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1231960B (en) * 1962-12-17 1967-01-05 Rolls Royce Combined gas turbine jet and ramjet engine
GB971222A (en) * 1962-12-17 1964-09-30 Rolls Royce Gas turbine power plant
US3630633A (en) * 1970-05-07 1971-12-28 Ford Motor Co Gas turbine engine nozzle actuation system
US8915703B2 (en) * 2011-07-28 2014-12-23 United Technologies Corporation Internally actuated inlet guide vane for fan section

Also Published As

Publication number Publication date
GB876504A (en) 1961-09-06

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