Rotating Detonating Engines (RDE) could provide performance improvements in the Gas Turbine thermal cycles. Since RDE uses detonative combustion, the outflow temperature and pressure are much higher than in traditional combustors and are highly unsteady. The harsh conditions represent a challenge for the turbine integration, with a high Mach number at the inlet of the turbine. In previous work, the CT3 HPT vane and endwalls were optimized to take in an averaged 0.6 Mach number. The diffusive endwalls and the elevated inlet Mach number require careful attention to the secondary flows generated in the vane, and its interaction with the stage’s rotor.