WO2015111998A1 - Procédé de fabrication et de contrôle d'un carénage pour turbines - Google Patents

Procédé de fabrication et de contrôle d'un carénage pour turbines Download PDF

Info

Publication number
WO2015111998A1
WO2015111998A1 PCT/MX2014/000024 MX2014000024W WO2015111998A1 WO 2015111998 A1 WO2015111998 A1 WO 2015111998A1 MX 2014000024 W MX2014000024 W MX 2014000024W WO 2015111998 A1 WO2015111998 A1 WO 2015111998A1
Authority
WO
WIPO (PCT)
Prior art keywords
turbine
hull
analysis
dimensional
design
Prior art date
Application number
PCT/MX2014/000024
Other languages
English (en)
Spanish (es)
Inventor
Luis Fernando TINAJERO AGUIRRE
Original Assignee
Tinajero Aguirre Luis Fernando
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 Tinajero Aguirre Luis Fernando filed Critical Tinajero Aguirre Luis Fernando
Priority to PCT/MX2014/000024 priority Critical patent/WO2015111998A1/fr
Publication of WO2015111998A1 publication Critical patent/WO2015111998A1/fr

Links

Classifications

    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01N—INVESTIGATING OR ANALYSING MATERIALS BY DETERMINING THEIR CHEMICAL OR PHYSICAL PROPERTIES
    • G01N25/00—Investigating or analyzing materials by the use of thermal means
    • G01N25/72—Investigating presence of flaws
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64F—GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT; DESIGNING, MANUFACTURING, ASSEMBLING, CLEANING, MAINTAINING OR REPAIRING AIRCRAFT, NOT OTHERWISE PROVIDED FOR; HANDLING, TRANSPORTING, TESTING OR INSPECTING AIRCRAFT COMPONENTS, NOT OTHERWISE PROVIDED FOR
    • B64F5/00—Designing, manufacturing, assembling, cleaning, maintaining or repairing aircraft, not otherwise provided for; Handling, transporting, testing or inspecting aircraft components, not otherwise provided for
    • B64F5/60—Testing or inspecting aircraft components or systems
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/04—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
    • F01D21/045—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position special arrangements in stators or in rotors dealing with breaking-off of part of rotor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J2005/0077—Imaging
    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01J—MEASUREMENT OF INTENSITY, VELOCITY, SPECTRAL CONTENT, POLARISATION, PHASE OR PULSE CHARACTERISTICS OF INFRARED, VISIBLE OR ULTRAVIOLET LIGHT; COLORIMETRY; RADIATION PYROMETRY
    • G01J5/00—Radiation pyrometry, e.g. infrared or optical thermometry
    • G01J5/0088—Radiation pyrometry, e.g. infrared or optical thermometry in turbines

Definitions

  • the present invention is applied in the formation of turbine hulls due to their high dimensional accuracy but the manufacturing process.
  • the present invention relates generally to a high precision manufacturing method and tooling and dimensional control of the containment hull of a turbine used in aircraft.
  • the turbines used in these devices have a fan and multiple fan blades arranged to rotate around a central axis. Catastrophic damage can occur to the aircraft and its occupants in case a broken fan blade is driven radially outward from the axis of rotation by force and impacts on the centrifuge of fuselage aircraft. To avoid these damages, it is common to include a generally cylindrical hull on the periphery to contain the fan blades. For engines of smaller diameter, adequate containment capability can be achieved with a simple metallic hull, thick enough to resist torque ⁇ penetration blade fragments. However, for larger diameter motors, a metal case thick enough to resist penetration is virtually impossible because of the weight that this implies. Moreover, these helmets have complicated geometries that demand very high precision and dimensional control.
  • the soft wall helmets use lightweight, high-strength, multi-layered structures around the structure.
  • a fragment of the turbine blade or blade will penetrate the support structure locally and strike but will not cut the fabric.
  • the tissue layers capture and contain the fragment.
  • Conventional support structures can be made of aluminum for weight considerations.
  • the support structure may include aluminum honeycomb structures.
  • US Pat. No. 0 6,053,696 proposes a composite material hull for the turbine.
  • the shell or composite shell includes two support rings structurally attached to a central portion that has an open lattice structure.
  • Other examples of fiber reinforced composite structures and manufacturing methods are provided in the following US patents.
  • UU. USA Pat. No. 0 4,086,378 to Kam et al.
  • Figure 1 Array of ultrasound sensors on the surface of the helmet and infrared cameras
  • the present invention describes a novel tool and method of manufacture of turbine hull for aircraft characterized by the following steps: Receive the specifications and dimensional tolerances corresponding to the characteristics required for a turbine hull of an aircraft: the selection of a wind capture of the design of the turbine case profile in accordance with the characteristics data received; the design, manufacture and validation of a structural support piece (1) whose external contact profile with said helmet (2) coincides with its internal surface with tolerance less than 1 thousandth of an inch; placing said mold (1) inside the structure of the hull of the turbine to be molded; placement of at least 6 vibration actuators (3) on the outer surface of the turbine hull; Capture video images per camera with at least three infrared sensor arrays (4) separated 120 degrees from each other; temperature uniformity analysis of thermal images per computer unit (5); evolution analysis of mechanical stress points;

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Transportation (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Health & Medical Sciences (AREA)
  • Life Sciences & Earth Sciences (AREA)
  • Chemical & Material Sciences (AREA)
  • Analytical Chemistry (AREA)
  • Biochemistry (AREA)
  • General Health & Medical Sciences (AREA)
  • General Physics & Mathematics (AREA)
  • Immunology (AREA)
  • Pathology (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Procédé de fabrication et de contrôle d'un carénage de protection contre les chocs internes pour une turbine d'un moteur d'aéronef. Ce procédé comprend les étapes suivantes; réception de spécifications et de tolérances, dessin, fabrication et validation d'une pièce de support structurale en tant que moule, mise en place dudit moule dans la structure de carénage, mise en place d'actionneurs vibrants à l'extérieur du carénage, capture d'images vidéo au moyen de caméras à infrarouge, analyse de l'uniformité de température des images thermiques, et analyse de l'évolution de la contrainte mécanique.
PCT/MX2014/000024 2014-01-27 2014-01-27 Procédé de fabrication et de contrôle d'un carénage pour turbines WO2015111998A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PCT/MX2014/000024 WO2015111998A1 (fr) 2014-01-27 2014-01-27 Procédé de fabrication et de contrôle d'un carénage pour turbines

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/MX2014/000024 WO2015111998A1 (fr) 2014-01-27 2014-01-27 Procédé de fabrication et de contrôle d'un carénage pour turbines

Publications (1)

Publication Number Publication Date
WO2015111998A1 true WO2015111998A1 (fr) 2015-07-30

Family

ID=53681715

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/MX2014/000024 WO2015111998A1 (fr) 2014-01-27 2014-01-27 Procédé de fabrication et de contrôle d'un carénage pour turbines

Country Status (1)

Country Link
WO (1) WO2015111998A1 (fr)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040089812A1 (en) * 2002-08-28 2004-05-13 Wayne State University System and method for multiple mode flexible excitation and acoustic chaos in sonic infrared imaging
US20080107147A1 (en) * 2006-11-06 2008-05-08 The Boeing Company Infrared ndi for shallow defect detection
US20090155044A1 (en) * 2007-12-12 2009-06-18 Ming Xie Composite containment casings having an integral fragment catcher
US20120034076A1 (en) * 2010-08-04 2012-02-09 General Electric Company Fan case containment system and method of fabrication

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040089812A1 (en) * 2002-08-28 2004-05-13 Wayne State University System and method for multiple mode flexible excitation and acoustic chaos in sonic infrared imaging
US20080107147A1 (en) * 2006-11-06 2008-05-08 The Boeing Company Infrared ndi for shallow defect detection
US20090155044A1 (en) * 2007-12-12 2009-06-18 Ming Xie Composite containment casings having an integral fragment catcher
US20120034076A1 (en) * 2010-08-04 2012-02-09 General Electric Company Fan case containment system and method of fabrication

Similar Documents

Publication Publication Date Title
JP6106587B2 (ja) ファンケース収納システムおよび作製方法
US9988156B2 (en) Cylindrical case and manufacturing method of cylindrical case
US8403624B2 (en) Composite containment casings having an integral fragment catcher
US9266603B2 (en) Single-piece propeller and method of making
ES2224807B1 (es) Conducto de reduccion de ruido para componentes estaticos de motores aeronauticos.
ES2650940T3 (es) Larguero de ala con varias cajas y revestimiento
US20180264749A1 (en) Shear Webs for Wind Turbine Rotor Blades and Methods for Manufacturing Same
ES2472890T3 (es) Procedimiento de realización de piezas compuestas de forma compleja
EP3476561A1 (fr) Moule modulaire et procédé de fabrication d'un panneau en matériau renforcé par des fibres
CN109113810B (zh) 具有蜂窝型负泊松比结构的发动机包容环及制造方法
EP2070689A2 (fr) Procédés de fabrication de boîtiers de confinement composite
US8371009B2 (en) Methods for repairing composite containment casings
US9296157B1 (en) Hybrid gear
BR112017003515B1 (pt) Invólucro de turbina a gás de material compósito, motor aeronáutico com turbina a gás, aeronave, e, método de fabricação de um invólucro de material compósito
ES2432567T3 (es) Estructura de material compuesto para fuselaje de aeronave y su procedimiento de fabricación
US20070031246A1 (en) Containment casing
WO2015111998A1 (fr) Procédé de fabrication et de contrôle d'un carénage pour turbines
JP2013542870A (ja) 複合構造体を製造する方法およびその方法によって得られる複合構造体
US10024301B2 (en) Textile composite wind turbine blade
US10648340B2 (en) High modulus hybrid material rotor blade spar
EP2851509B1 (fr) Fabrication de surface portante creuse
ES2425026B1 (es) Método de fabricación de un componente de una pala partida de un aerogenerador
US20090151162A1 (en) Methods for making composite containment casings having an integral fragment catcher
RU2595354C1 (ru) Корпус гиперзвукового летательного аппарата и способ его изготовления
US12006874B2 (en) 3D printed acoustic panel with lattice structure support layer

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 14879622

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

122 Ep: pct application non-entry in european phase

Ref document number: 14879622

Country of ref document: EP

Kind code of ref document: A1