IT1162720B - Perfezionamenti apportati alle palette direttrici per motori a turbina a gas - Google Patents

Perfezionamenti apportati alle palette direttrici per motori a turbina a gas

Info

Publication number
IT1162720B
IT1162720B IT21209/79A IT2120979A IT1162720B IT 1162720 B IT1162720 B IT 1162720B IT 21209/79 A IT21209/79 A IT 21209/79A IT 2120979 A IT2120979 A IT 2120979A IT 1162720 B IT1162720 B IT 1162720B
Authority
IT
Italy
Prior art keywords
refinements
supplied
gas turbine
turbine engines
vane
Prior art date
Application number
IT21209/79A
Other languages
English (en)
Other versions
IT7921209A0 (it
Original Assignee
Rolls Royce
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 filed Critical Rolls Royce
Publication of IT7921209A0 publication Critical patent/IT7921209A0/it
Application granted granted Critical
Publication of IT1162720B publication Critical patent/IT1162720B/it

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
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
IT21209/79A 1978-03-22 1979-03-22 Perfezionamenti apportati alle palette direttrici per motori a turbina a gas IT1162720B (it)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB1152978 1978-03-22
GB7907474A GB2017229B (en) 1978-03-22 1979-03-02 Guides vanes for gas turbine enginess

Publications (2)

Publication Number Publication Date
IT7921209A0 IT7921209A0 (it) 1979-03-22
IT1162720B true IT1162720B (it) 1987-04-01

Family

ID=26248339

Family Applications (1)

Application Number Title Priority Date Filing Date
IT21209/79A IT1162720B (it) 1978-03-22 1979-03-22 Perfezionamenti apportati alle palette direttrici per motori a turbina a gas

Country Status (2)

Country Link
GB (1) GB2017229B (it)
IT (1) IT1162720B (it)

Families Citing this family (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2473621A1 (fr) * 1980-01-10 1981-07-17 Snecma Aube de distributeur de turbine
US4312624A (en) * 1980-11-10 1982-01-26 United Technologies Corporation Air cooled hollow vane construction
GB2163218B (en) * 1981-07-07 1986-07-16 Rolls Royce Cooled vane or blade for a gas turbine engine
GB2119028B (en) * 1982-04-27 1985-02-27 Rolls Royce Aerofoil for a gas turbine engine
US4798515A (en) * 1986-05-19 1989-01-17 The United States Of America As Represented By The Secretary Of The Air Force Variable nozzle area turbine vane cooling
US5203873A (en) * 1991-08-29 1993-04-20 General Electric Company Turbine blade impingement baffle
GB2343486B (en) 1998-06-19 2000-09-20 Rolls Royce Plc Improvemnts in or relating to cooling systems for gas turbine engine airfoil
US6238182B1 (en) * 1999-02-19 2001-05-29 Meyer Tool, Inc. Joint for a turbine component
GB2366599B (en) * 2000-09-09 2004-10-27 Rolls Royce Plc Gas turbine engine system
GB2386926A (en) * 2002-03-27 2003-10-01 Alstom Two part impingement tube for a turbine blade or vane
GB2441771B (en) * 2006-09-13 2009-07-08 Rolls Royce Plc Cooling arrangement for a component of a gas turbine engine
JP4995141B2 (ja) * 2008-05-08 2012-08-08 三菱重工業株式会社 タービン用翼構造
US20140093379A1 (en) * 2012-10-03 2014-04-03 Rolls-Royce Plc Gas turbine engine component
EP2860348A1 (de) * 2013-10-08 2015-04-15 Siemens Aktiengesellschaft Einsatz für eine Turbinenschaufel aus mehreren Bauteilen und zugehöriges Verfahren
US10329932B2 (en) 2015-03-02 2019-06-25 United Technologies Corporation Baffle inserts
US10781715B2 (en) 2015-12-21 2020-09-22 Raytheon Technologies Corporation Impingement cooling baffle
US10502070B2 (en) 2016-11-17 2019-12-10 United Technologies Corporation Airfoil with laterally insertable baffle

Also Published As

Publication number Publication date
GB2017229B (en) 1982-07-14
GB2017229A (en) 1979-10-03
IT7921209A0 (it) 1979-03-22

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