Nova Patents
RU2012123451A

Flexible support structure for a geared architecture gas turbine engine

Abstract

one. Drive design for gas turbine engine, comprising: fan shaft; frame, supporting fan shaft and setting reference transverse stiffness (Kframe); gear system, rotational fan shaft; flexible load-bearing structure, at least partially supporting gear system and having lateral rigidity (KFS), defined relative to the transverse stiffness (Kframe) of the frame, input unit of the gear system, having transverse stiffness (KIC), defined relative to the transverse stiffness (Kframe) of the frame. 2. The construction according to claim 1, wherein the frame and the flexible supporting structure are mounted on the static structure. The construction according to claim 1, wherein the frame and the flexible supporting structure are mounted on a static structure as part of a gas turbine engine. The construction according to claim 1, in which the frame and the flexible supporting structure are mounted on the front central part of the casing of the gas turbine engine. The construction according to claim 1, in which the flexible supporting structure is connected with the carrier of planetary gears of the gear system. The construction according to claim 5, in which the input node is connected to the sun gear of the gear system. The construction according to claim 6, in which the fan shaft is connected to the ring gear of the gear system. The construction according to claim 7, in which the gear system is a planetary system with a stationary carrier. The construction according to claim 1, in which a flexible supporting structure is connected with the ring gear of the gear system. The construction according to claim 9, in which the input node is connected to the sun gear of the gear system. The structure of claim 10, wherein the fan shaft is coupled to the planet carrier of the gear system. The construction according to

Term

5.7 yearsto projected expiry

Projected expiry 7 June 2032, counted from filing; an application has no term until it is granted.

  1. Priority
  2. Filed
  3. Published
  4. Today
  5. Projected expiry

34 claims: 12 independent, 22 dependent

  1. 1
    The drive structure for a gas turbine engine, comprising:1. Приводная конструкция для газотурбинного двигателя, содержащая:
  2. 2
    The fan shaft;2. вал вентилятора;
  3. 3
    The frame that supports the fan shaft and defining a frame lateral stiffness (KframeBEND);3. раму, поддерживающую вал вентилятора и задающую репер поперечной жесткости (KframeBEND);
  4. 4
    The gear system, resulting in the rotation of the fan shaft;4. зубчатую систему, приводящую во вращение вал вентилятора;
  5. 5
    The flexible support structure at least partially supporting the gear system and having lateral stiffness (KFSBEND), Determined by the relative lateral stiffness (KframeBEND) Frame, and 5. гибкую несущую конструкцию, по меньшей мере частично поддерживающую зубчатую систему и имеющую поперечную жесткость (KFSBEND), определяемую относительно поперечной жесткости (KframeBEND) рамы, и
  6. 6
    The input gear system assembly having lateral stiffness (KICBEND), Determined by the relative lateral stiffness (KframeBEND) Frame. 6. входной узел зубчатой системы, имеющий поперечную жесткость (KICBEND), определяемую относительно поперечной жесткости (KframeBEND) рамы.
  7. 23
    18. Drive structure for a gas turbine engine, comprising:18. Приводная конструкция для газотурбинного двигателя, содержащая:
  8. 24
    The fan shaft;24. вал вентилятора;
  9. 25
    The frame that supports the fan shaft;25. раму, поддерживающую вал вентилятора;
  10. 26
    The gear system, resulting in rotation of the fan shaft and having gear teeth having transverse rigidity (KGMBEND);26. зубчатую систему, приводящую во вращение вал вентилятора и содержащую зубчатое зацепление, имеющее поперечную жесткость (KGMBEND);
  11. 27
    The flexible support structure at least partially supporting the gear system and having lateral stiffness (KFSBEND), Determined by the relative lateral stiffness (KGMBEND) Gearing and 27. гибкую несущую конструкцию, по меньшей мере частично поддерживающую зубчатую систему и имеющую поперечную жесткость (KFSBEND), определяемую относительно поперечной жесткости (KGMBEND) зубчатого зацепления, и
  12. 28
    The system of the input gear assembly having lateral stiffness (KICBEND), Determined by the relative lateral stiffness (KGMBEND) Gearing. 28. входной узел зубчатой системы, имеющий поперечную жесткость (KICBEND), определяемую относительно поперечной жесткости (KGMBEND) зубчатого зацепления.
Independent claims12