FR2986046A1 - Ring assembly for rotor of blower in turbojet of airplane, has air inlet cone fixed directly on ring by screws, where screws comprise heads placed in recesses of cone and leveled with outer wall of cone, and ring is fixed upstream of disk - Google Patents

Ring assembly for rotor of blower in turbojet of airplane, has air inlet cone fixed directly on ring by screws, where screws comprise heads placed in recesses of cone and leveled with outer wall of cone, and ring is fixed upstream of disk Download PDF

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Publication number
FR2986046A1
FR2986046A1 FR1250686A FR1250686A FR2986046A1 FR 2986046 A1 FR2986046 A1 FR 2986046A1 FR 1250686 A FR1250686 A FR 1250686A FR 1250686 A FR1250686 A FR 1250686A FR 2986046 A1 FR2986046 A1 FR 2986046A1
Authority
FR
France
Prior art keywords
cone
ring
screws
blower
rotor
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.)
Granted
Application number
FR1250686A
Other languages
French (fr)
Other versions
FR2986046B1 (en
Inventor
Frederic Rogues
Benjamin Kiener-Calvet
Wouter Balk
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.)
Safran Aircraft Engines SAS
Safran SA
Original Assignee
Safran SA
SNECMA SAS
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 Safran SA, SNECMA SAS filed Critical Safran SA
Priority to FR1250686A priority Critical patent/FR2986046B1/en
Publication of FR2986046A1 publication Critical patent/FR2986046A1/en
Application granted granted Critical
Publication of FR2986046B1 publication Critical patent/FR2986046B1/en
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Anticipated expiration legal-status Critical

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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
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B64C11/02—Hub construction
    • B64C11/14—Spinners
    • 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
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/20—Adaptations of gas-turbine plants for driving vehicles
    • F02C6/206—Adaptations of gas-turbine plants for driving vehicles the vehicles being airscrew driven
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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
    • 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
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

The assembly has a ring (3) to be fixed upstream of a disk, and an air inlet cone (9) mounted upstream of the ring. The air inlet cone is fixed directly on the ring by fixation units i.e. screws (18). The screws comprise heads (25) placed in recesses (37, 38) of the cone and leveled with an outer wall (21) of the cone. The screws are screwed into nuts (17) mounted in holes (32) of a part (28) of the ring. The cone has an inner wall (22) comprising a cylindrical centering part (35) located at the level of a downstream end (36) of the cone. Independent claims are also included for the following: (1) a rotor of a blower (2) a method for disassembling a rotor of a blower.
FR1250686A 2012-01-24 2012-01-24 ASSEMBLY FOR A TURBOMACHINE BLOWER ROTOR Active FR2986046B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1250686A FR2986046B1 (en) 2012-01-24 2012-01-24 ASSEMBLY FOR A TURBOMACHINE BLOWER ROTOR

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1250686A FR2986046B1 (en) 2012-01-24 2012-01-24 ASSEMBLY FOR A TURBOMACHINE BLOWER ROTOR

Publications (2)

Publication Number Publication Date
FR2986046A1 true FR2986046A1 (en) 2013-07-26
FR2986046B1 FR2986046B1 (en) 2016-01-08

Family

ID=46044885

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1250686A Active FR2986046B1 (en) 2012-01-24 2012-01-24 ASSEMBLY FOR A TURBOMACHINE BLOWER ROTOR

Country Status (1)

Country Link
FR (1) FR2986046B1 (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015023325A1 (en) 2013-08-12 2015-02-19 United Technologies Corporation Non-axisymmetric fan flow path
FR3063308A1 (en) * 2017-02-24 2018-08-31 Safran Aircraft Engines CAP FOR TURBOMACHINE ROTATING INPUT COVER, COMPRISING AERODYNAMIC EXTERNAL WALL AND CONE FASTENER
FR3084697A1 (en) * 2018-07-31 2020-02-07 Safran Aircraft Engines Improved balancing system for aircraft turbomachines
CN111852906A (en) * 2019-04-28 2020-10-30 中国航发商用航空发动机有限责任公司 Aircraft engine fan device and aircraft engine
US10975720B2 (en) 2018-07-31 2021-04-13 Safran Aircraft Engines Balancing system for an aircraft turbomachine
FR3108149A1 (en) 2020-03-11 2021-09-17 Safran Aircraft Engines BLOWER MODULE FOR AN AIRCRAFT TURBOMACHINE
FR3120852A1 (en) 2021-03-18 2022-09-23 Safran Aircraft Engines ATTACHING A FRONT CONE WITH ENHANCED AERODYNAMICS
FR3137414A1 (en) * 2022-07-04 2024-01-05 Safran Aircraft Engines INLET CONE FOR AIRCRAFT TURBOMACHINE

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3735471A (en) * 1971-12-17 1973-05-29 D Kappler Device for removing a fan from a shaft
EP2096029A2 (en) * 2008-02-26 2009-09-02 Rolls-Royce plc Nose cone assembly and gas turbine engine comprising such an assemby
EP2161431A2 (en) * 2008-09-03 2010-03-10 Rolls-Royce Deutschland Ltd & Co KG Inlet nose cone for an aircraft gas turbine powerplant
US20100260605A1 (en) * 2009-04-10 2010-10-14 Macfarlane Russel Balance weight
US20110085914A1 (en) * 2009-10-14 2011-04-14 Rolls-Royce Plc Annulus filler element for a rotor of a turbomachine

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3735471A (en) * 1971-12-17 1973-05-29 D Kappler Device for removing a fan from a shaft
EP2096029A2 (en) * 2008-02-26 2009-09-02 Rolls-Royce plc Nose cone assembly and gas turbine engine comprising such an assemby
EP2161431A2 (en) * 2008-09-03 2010-03-10 Rolls-Royce Deutschland Ltd & Co KG Inlet nose cone for an aircraft gas turbine powerplant
US20100260605A1 (en) * 2009-04-10 2010-10-14 Macfarlane Russel Balance weight
US20110085914A1 (en) * 2009-10-14 2011-04-14 Rolls-Royce Plc Annulus filler element for a rotor of a turbomachine

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015023325A1 (en) 2013-08-12 2015-02-19 United Technologies Corporation Non-axisymmetric fan flow path
EP3033497A1 (en) * 2013-08-12 2016-06-22 United Technologies Corporation Non-axisymmetric fan flow path
EP3033497A4 (en) * 2013-08-12 2017-03-29 United Technologies Corporation Non-axisymmetric fan flow path
US10415505B2 (en) 2013-08-12 2019-09-17 United Technologies Corporation Non-axisymmetric fan flow path
FR3063308A1 (en) * 2017-02-24 2018-08-31 Safran Aircraft Engines CAP FOR TURBOMACHINE ROTATING INPUT COVER, COMPRISING AERODYNAMIC EXTERNAL WALL AND CONE FASTENER
US10487736B2 (en) 2017-02-24 2019-11-26 Safran Aircraft Engines Plug for rotating inlet cowl of a turbo machine including an aerodynamic external wall and a cone attachment element
FR3084697A1 (en) * 2018-07-31 2020-02-07 Safran Aircraft Engines Improved balancing system for aircraft turbomachines
FR3084696A1 (en) * 2018-07-31 2020-02-07 Safran Aircraft Engines IMPROVED BALANCING SYSTEM FOR AN AIRCRAFT TURBOMACHINE
US10975720B2 (en) 2018-07-31 2021-04-13 Safran Aircraft Engines Balancing system for an aircraft turbomachine
CN111852906A (en) * 2019-04-28 2020-10-30 中国航发商用航空发动机有限责任公司 Aircraft engine fan device and aircraft engine
CN111852906B (en) * 2019-04-28 2022-02-22 中国航发商用航空发动机有限责任公司 Aircraft engine fan device and aircraft engine
FR3108149A1 (en) 2020-03-11 2021-09-17 Safran Aircraft Engines BLOWER MODULE FOR AN AIRCRAFT TURBOMACHINE
FR3120852A1 (en) 2021-03-18 2022-09-23 Safran Aircraft Engines ATTACHING A FRONT CONE WITH ENHANCED AERODYNAMICS
FR3137414A1 (en) * 2022-07-04 2024-01-05 Safran Aircraft Engines INLET CONE FOR AIRCRAFT TURBOMACHINE

Also Published As

Publication number Publication date
FR2986046B1 (en) 2016-01-08

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