Over-all performance of J35-A-23 two-stage turbine

Rebeske, John J., Jr., Berkey, William E., Forrette, Robert E.
naca-rm-e51e22
1951


Over-all performance of a two-stage turbine from a J35-A-23 turbojet engine is presented. Limiting blade loading restricted work output to approximately 95 percent of the design value. The brake internal efficiency at design operating conditions was approximately 0.75. maximum brake internal efficiency at off-design conditions was between 0.81 and 0.82.

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