Claims
- 1. A rotor assembly for a gas turbine engine, comprising:
- a disc having along its periphery circumferentially spaced dovetail grooves,
- a blade having an airfoil portion and a root portion, said root portion contoured to be received within said dovetail groove and having an inner surface that extends axially from a leading edge to a trailing edge, said leading and trailing edges each having a tab member extending inward therefrom to define a gap between said inner surface and a base of said groove; and
- an elastomeric member disposed in said gap and having a top surface bonded to said inner surface of said root portion and a bottom surface having two portions inclined at an angle and spaced apart to define a surface portion therebetween for sealingly contacting said base of said groove.
- 2. The rotor assembly of claim 1 wherein said elastomeric member has a top surface shaped as a parallelogram.
- 3. The rotor assembly of claim 2 wherein said top surface has curved longitudinal edges.
- 4. The rotor assembly of claim 1 wherein said elastomeric member has the following properties;
- ______________________________________ After Aging for 7 Days After Curing at 500.degree. F.______________________________________Hardness, Shore A 70 85 maxTensile Strength, psi 750 min 600 minElongation 60% min. 70% minCompression Set after 60.22 hrs at 500.degree. F., and25% deflection______________________________________
Parent Case Info
This application is a continuation of application Ser. No. 08/253,439 filed Jun. 7, 1994, now abandoned.
US Referenced Citations (18)
Continuations (1)
|
Number |
Date |
Country |
Parent |
253439 |
Jun 1994 |
|