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RU2011141460A - AXIAL-CENTRIFUGAL COMPRESSOR WITH VARIABLE ANGLE OF SLOPE OF THE SHOVEL - Google Patents

AXIAL-CENTRIFUGAL COMPRESSOR WITH VARIABLE ANGLE OF SLOPE OF THE SHOVEL Download PDF

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Publication number
RU2011141460A
RU2011141460A RU2011141460/06A RU2011141460A RU2011141460A RU 2011141460 A RU2011141460 A RU 2011141460A RU 2011141460/06 A RU2011141460/06 A RU 2011141460/06A RU 2011141460 A RU2011141460 A RU 2011141460A RU 2011141460 A RU2011141460 A RU 2011141460A
Authority
RU
Russia
Prior art keywords
trailing edge
blade
movable wheel
root
compressor
Prior art date
Application number
RU2011141460/06A
Other languages
Russian (ru)
Inventor
Жоффруа Луис Анри БИЙОТЕЙ
Жан-Филипп УСТИ
Николас РОШЮОН
Original Assignee
Турбомека
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 Турбомека filed Critical Турбомека
Publication of RU2011141460A publication Critical patent/RU2011141460A/en

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/30—Vanes
    • 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
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/04—Blade-carrying members, e.g. rotors for radial-flow machines or engines
    • F01D5/043—Blade-carrying members, e.g. rotors for radial-flow machines or engines of the axial inlet- radial outlet, or vice versa, type
    • F01D5/048—Form or construction
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
    • F04D29/284—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps for compressors
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—Blades
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1. Подвижное колесо для компрессора центробежного типа или смешанного аксиально-центробежного типа для газотурбинного двигателя, содержащее цоколь (2), на котором закрепляются своими корневыми частями (6) множество лопаток (3), проходящих между передней кромкой (8) и задней кромкой (9), причем упомянутая задняя кромка наклонена на уровне корневой части (6) лопатки (3) на некоторый угол α по отношению к средней плоскости, которая пересекает лопатку в ее корневой части в направлении вращения упомянутого компрессора (1), отличающееся тем, что упомянутая задняя кромка (9) представляет на уровне верхней части (7) лопатки (3) угол наклона β, меньший, чем ее угол наклона α в корневой части лопатки.2. Подвижное колесо по п.1, в котором угол наклона β задней кромки (9) на уровне верхней части лопатки является близким к нулю и даже нулевым.3. Подвижное колесо по п.1, в котором угол наклона β задней кромки (9) на уровне верхней части лопатки является отрицательным.4. Подвижное колесо по п.1, в котором кривизна задней кромки (9) является постоянной между корневой частью (6) и верхней частью (7) упомянутой задней кромки.5. Подвижное колесо по п.1, в котором кривизна задней кромки (9) является непрерывно изменяющейся между корневой частью (9) и верхней частью (7) упомянутой задней кромки.6. Компрессор, имеющий в своем составе подвижное колесо в соответствии с п.1.7. Газотурбинный двигатель, имеющий в своем составе компрессор в соответствии с п.6.8. Воздушное судно, оборудованное газотурбинным двигателем в соответствии с предшествующим пунктом.1. A movable wheel for a compressor of a centrifugal type or a mixed axial-centrifugal type for a gas turbine engine, containing a base (2), on which a plurality of blades (3) are fixed with their root parts (6), passing between the leading edge (8) and the trailing edge ( 9), and said trailing edge is inclined at the level of the root part (6) of the blade (3) at a certain angle α with respect to the median plane that intersects the blade in its root part in the direction of rotation of the said compressor (1), characterized in that the mentioned the trailing edge (9) represents at the level of the upper part (7) of the blade (3) an angle of inclination β, which is less than its angle of inclination α in the root part of the blade. 2. A movable wheel according to claim 1, in which the inclination angle β of the trailing edge (9) at the level of the upper part of the blade is close to zero or even zero. A movable wheel according to claim 1, wherein the inclination angle β of the trailing edge (9) at the level of the upper part of the blade is negative. A movable wheel according to claim 1, wherein the curvature of the trailing edge (9) is constant between the root portion (6) and the upper portion (7) of said trailing edge. A movable wheel according to claim 1, wherein the curvature of the trailing edge (9) is continuously changing between the root portion (9) and the upper portion (7) of said trailing edge. Compressor with a movable wheel in accordance with clause 1.7. Gas turbine engine incorporating a compressor in accordance with clause 6.8. An aircraft equipped with a gas turbine engine in accordance with the preceding paragraph.

Claims (8)

1. Подвижное колесо для компрессора центробежного типа или смешанного аксиально-центробежного типа для газотурбинного двигателя, содержащее цоколь (2), на котором закрепляются своими корневыми частями (6) множество лопаток (3), проходящих между передней кромкой (8) и задней кромкой (9), причем упомянутая задняя кромка наклонена на уровне корневой части (6) лопатки (3) на некоторый угол α по отношению к средней плоскости, которая пересекает лопатку в ее корневой части в направлении вращения упомянутого компрессора (1), отличающееся тем, что упомянутая задняя кромка (9) представляет на уровне верхней части (7) лопатки (3) угол наклона β, меньший, чем ее угол наклона α в корневой части лопатки.1. A movable wheel for a centrifugal type compressor or a mixed axial-centrifugal type for a gas turbine engine, comprising a socle (2) on which a plurality of vanes (3) are fixed with their root parts (6), passing between the leading edge (8) and the trailing edge ( 9), wherein said trailing edge is inclined at the level of the root part (6) of the blade (3) by a certain angle α with respect to the middle plane that intersects the blade in its root part in the direction of rotation of said compressor (1), characterized in that Single trailing edge (9) is at the level of the upper part (7) of the blade (3) the tilt angle β, smaller than its angle α at the blade root. 2. Подвижное колесо по п.1, в котором угол наклона β задней кромки (9) на уровне верхней части лопатки является близким к нулю и даже нулевым.2. The movable wheel according to claim 1, in which the angle of inclination β of the trailing edge (9) at the level of the upper part of the blade is close to zero and even zero. 3. Подвижное колесо по п.1, в котором угол наклона β задней кромки (9) на уровне верхней части лопатки является отрицательным.3. The movable wheel according to claim 1, in which the angle of inclination β of the trailing edge (9) at the level of the upper part of the blade is negative. 4. Подвижное колесо по п.1, в котором кривизна задней кромки (9) является постоянной между корневой частью (6) и верхней частью (7) упомянутой задней кромки.4. The movable wheel according to claim 1, in which the curvature of the trailing edge (9) is constant between the root part (6) and the upper part (7) of said trailing edge. 5. Подвижное колесо по п.1, в котором кривизна задней кромки (9) является непрерывно изменяющейся между корневой частью (9) и верхней частью (7) упомянутой задней кромки.5. The movable wheel according to claim 1, in which the curvature of the trailing edge (9) is continuously changing between the root part (9) and the upper part (7) of said trailing edge. 6. Компрессор, имеющий в своем составе подвижное колесо в соответствии с п.1.6. A compressor having a movable wheel in accordance with claim 1. 7. Газотурбинный двигатель, имеющий в своем составе компрессор в соответствии с п.6.7. A gas turbine engine incorporating a compressor in accordance with paragraph 6. 8. Воздушное судно, оборудованное газотурбинным двигателем в соответствии с предшествующим пунктом. 8. An aircraft equipped with a gas turbine engine in accordance with the preceding paragraph.
RU2011141460/06A 2009-03-13 2010-03-10 AXIAL-CENTRIFUGAL COMPRESSOR WITH VARIABLE ANGLE OF SLOPE OF THE SHOVEL RU2011141460A (en)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR0951604A FR2943103B1 (en) 2009-03-13 2009-03-13 AXIALO-CENTRIFUGAL COMPRESSOR WITH AN EVOLVING RAKE ANGLE
FR0951604 2009-03-13
PCT/EP2010/053057 WO2010103055A1 (en) 2009-03-13 2010-03-10 Axial centrifugal compressor with scalable rake angle

Publications (1)

Publication Number Publication Date
RU2011141460A true RU2011141460A (en) 2013-04-20

Family

ID=41057639

Family Applications (1)

Application Number Title Priority Date Filing Date
RU2011141460/06A RU2011141460A (en) 2009-03-13 2010-03-10 AXIAL-CENTRIFUGAL COMPRESSOR WITH VARIABLE ANGLE OF SLOPE OF THE SHOVEL

Country Status (9)

Country Link
US (1) US20110318188A1 (en)
EP (1) EP2406500A1 (en)
JP (1) JP5687215B2 (en)
KR (1) KR101746870B1 (en)
CN (1) CN102341602B (en)
CA (1) CA2755017C (en)
FR (1) FR2943103B1 (en)
RU (1) RU2011141460A (en)
WO (1) WO2010103055A1 (en)

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JP5705945B1 (en) * 2013-10-28 2015-04-22 ミネベア株式会社 Centrifugal fan
US10634157B2 (en) 2014-01-07 2020-04-28 Nuovo Pignone Srl Centrifugal compressor impeller with non-linear leading edge and associated design method
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Also Published As

Publication number Publication date
KR101746870B1 (en) 2017-06-14
KR20110129465A (en) 2011-12-01
JP2012520412A (en) 2012-09-06
FR2943103B1 (en) 2011-05-27
CN102341602B (en) 2015-07-01
US20110318188A1 (en) 2011-12-29
EP2406500A1 (en) 2012-01-18
CA2755017A1 (en) 2010-09-16
CA2755017C (en) 2017-04-04
FR2943103A1 (en) 2010-09-17
JP5687215B2 (en) 2015-03-18
WO2010103055A1 (en) 2010-09-16
CN102341602A (en) 2012-02-01

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