STATOR PLATED DESIGN AND TURBOFAN ENGINE USING IT Russian patent published in 2018 - IPC F01D11/00 F04D29/54 F01D9/04 

Abstract RU 2672545 C2

FIELD: machine building.

SUBSTANCE: proposed stator plated design, which can suppress the pressure loss caused by the gap or level difference between the liners forming the air channel with stator vanes made of composite material and liners in the turbofan engine, and a turbofan engine using this stator flap design. Inner liners (40) are adjacent to each other with clamping between them base part (21) of output guide blade (stator blade) (20) of fan made of composite material, outer liners (50) are adjacent to each other with clamping between them end part (22) of output guide vanes (20) of fan, respectively, and dividing lines (45, 46, 55, 56), which are formed between these liners on the side of the inlet edge, run along the direction of flow.

EFFECT: it is possible to suppress the pressure loss caused by the gap or the level difference between the liners, since the air channel is formed using stator vanes made of composite material and liners.

3 cl, 6 dwg

Similar patents RU2672545C2

Title Year Author Number
DUAL-FLOW TURBOJET ENGINE 2015
  • Kanakhin Yurij Aleksandrovich
  • Marchukov Evgenij Yuvenalevich
  • Starodumova Irina Mikhajlovna
RU2618993C1
LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE 2016
  • Marchukov Evgenij Yuvenalevich
  • Erichev Dmitrij Yurevich
  • Ilyasov Sergej Anatolevich
  • Kuprik Viktor Viktorovich
  • Savchenko Aleksandr Gavrilovich
  • Shishkova Olga Vladimirovna
  • Selivanov Nikolaj Pavlovich
RU2614709C1
ROTOR WITH INTEGRATED DESIGN OF BLADE SET 1998
  • Rossmann Aksel'
  • Sikorski Zigfrid
  • Krjuger Vol'Fgang
RU2221922C2
LOW-PRESSURE COMPRESSOR OF GAS TURBINE ENGINE OF AVIATION TYPE 2016
  • Marchukov Evgenij Yuvenalevich
  • Ilyasov Sergej Anatolevich
  • Kuprik Viktor Viktorovich
  • Konovalova Tamara Petrovna
  • Polyakov Konstantin Sergeevich
  • Savchenko Aleksandr Gavrilovich
  • Skaryakina Regina Yurevna
  • Selivanov Nikolaj Pavlovich
RU2614708C1
FAN ROTOR BLADE OF JET ENGINE FOR AIRCRAFT 2013
  • Yagi Khiroyuki
  • Kuroki Khirosi
  • Obuti Kenro
RU2599219C2
FAN ROTOR BLADE OF AIRCRAFT JET ENGINE 2013
  • Yagi Khiroyuki
  • Kuroki Khirosi
  • Obuti Kenro
RU2592365C2
METHOD OF COOLING THE ROTOR OF A HIGH PRESSURE TURBINE (HPT) OF GAS TURBINE ENGINE (GTE), HPT ROTOR AND HPT ROTOR BLADE COOLED BY THIS METHOD, KNOT OF THE DEVICE OF TWISTING OF AIR OF HPT ROTOR 2018
  • Marchukov Evgenij Yuvenalevich
  • Kuprik Viktor Viktorovich
  • Andreev Viktor Andreevich
  • Komarov Mikhail Yurevich
  • Kononov Nikolaj Aleksandrovich
  • Selivanov Nikolaj Pavlovich
RU2684298C1
COMPRESSOR BLADE 2018
  • Bruni, Giuseppe
  • Krishnababu, Senthil
RU2729590C1
DOUBLE-FLOW GAS TURBINE ENGINE 2011
  • Kanakhin Jurij Aleksandrovich
  • Kirjukhin Vladimir Valentinovich
  • Marchukov Evgenij Juvenal'Evich
  • Starodumova Irina Mikhajlovna
RU2459967C1
AXIAL COMPRESSOR BLADE MAKING METHOD 1999
  • Gritsenko E.A.
  • Klimnjuk Ju.I.
  • Lazorenko T.M.
  • Fedorchenko D.G.
  • Ignachkov S.M.
RU2176335C2

RU 2 672 545 C2

Authors

Enoki, Tomonori

Inada, Takaomi

Kajiwara, Rintarou

Yagi, Hiroyuki

Dates

2018-11-15Published

2015-10-01Filed