System for balancing and damping a turbojet engine disk

• US 5,582,077 A
• Filed: 02/23/1995
• Issued: 12/10/1996
• Est. Priority Date: 03/03/1994
• Status: Expired due to Term

• Current Assignee: Snecma (Safran SA)
• Original Assignee: Societe Nationale dEtude et de Construction de Moteurs dAviation SNECMA (Safran SA)
• Inventors: Bodet, Philippe, Agram, Daniel A., Prigent, Gerard D., Dhyser, Fran.cedilla.ois G.
• Primary Examiner(s): NOT, DEFINED
• Assistant Examiner(s): Kim, Chong H.
• Application Number:
  US08/393,358
• Time in Patent Office: 656 Days
• Field of Search: 74/572, 74/573 R, 416/144, 416/145, 285/376, 285/377, 403/316, 403/317, 403/318, 403/348
• US Class Current: 464/180
• CPC Class Codes: F01D 5/027 Arrangements for balancing for balancing rotating bodies in general F16F15/32; for compensating unbalance G01M1/36
• CPC Class Codes: F01D 5/10 Anti- vibration means specially adapted for radial flow machines or engines F01D5/04
• CPC Class Codes: F16B 2200/69 Redundant disconnection blocking means
• CPC Class Codes: F16F 15/32 Correcting- or balancing-weights or equivalent means for balancing rotating bodies, e.g. vehicle wheels suppression of vibrations in rotating systems by using freely rotating masses F16F15/14; compensation of inertia forces F16F15/22; compensating unbalance for testing purposes G01M1/30
• CPC Class Codes: Y10T 403/7005 Lugged member, rotary engagement

Abstract

A rotor disk arrangement for a turbojet engine includes a balancing and damping system which has a ring having a circumferential surface recessed with housings and balance masses respectively positioned in the housings. A disk having a circumferential surface is provided which engages the circumferential surface of the ring. The circumferential surfaces are provided with a plurality of bayonet couplings, the couplings including a tenon and a groove engaged with the tenon. The groove includes a straight entrance portion which is substantially parallel to the axis of the engine and a crooked hind part which is substantially circumferentially positioned in the engine. In addition, a plurality of tongues are provided which are respectively inserted into the entrance portions of the grooves and fastened to the ring.

Claims

1. A rotor disk arrangement for a turbojet engine, which comprises:

a balancing and damping system comprising a ring having a circumferential surface recessed with housings and balance masses respectively positioned in said housings;

a disk having a circumferential surface which engages the circumferential surface of the ring wherein the circumferential surfaces of the disk and ring comprise a plurality of bayonet couplings, said couplings including a tenon and a groove engaged by the tenon for each of the bayonet couplings, the groove comprising a straight entrance portion which is substantially parallel to an axis of the engine and a crooked hind part which is substantially circumferentially positioned in the engine; and

a plurality of tongues respectively inserted into the entrance portions of the grooves and fastened to the ring.

2. A rotor disk arrangement according to claim 1, which comprises a gasket covering a flat surface portion of the ring which faces away from the disk wherein the tongues are integrally connected with said gasket, and wherein the housings opening on said flat surface and the gasket are fastened to the ring by bolts engaging the gasket.

3. A rotor disk arrangement according to claim 1, wherein the tenons are provided on the disk and the grooves are formed in the ring.

4. A rotor disk arrangement according to claim 2, wherein the ring has a plurality of lugs with apertures formed therein and the bolts are respectively located in the apertures of the lugs.