ROTOR BLADE FOR GAS TURBINE ENGINES
Assignee
Filed
Sep 30, 1975
Granted
Nov 8, 1983
Location
Abstract
A turbine blade for a gas turbine engine has a hollow aerofoil and a root. A first insert for the distribution of cooling air in the aerofoil is inserted thereinto through an opening in the root but due to the relatively high camber of the blade the insert is such that it has to be displaced laterally after insertion. A second insert, also inserted through the opening, is provided to secure the first insert in position and to guide the cooling air from the opening to the first insert.
Source: Google Patents
35 USC §181 Secrecy Order
Imposed
Oct 1, 1982
Rescinded
Dec 29, 1982
Duration
2 months
Record Details
- Patent number
- US 4413949
- Application
- 05618688
- Aerospace match
- Yes
- Dataset source
- 35 USC §181 SO records
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