A semivaneless turbine stator designed to eliminate blade wakes and secondary-flow accumulations of boundary-layer air was built and tested. Performance of this stator was evaluated with static pressures measured in the vaneless section and surveys of total pressure and flow angle made at the stator exit. Results are presented in terms of theoretical and experimental velocities and flow angles, boundary-layer parameters, and contours of total-pressure loss across the stator
ABSTRACT Midspan aerodynamic measurements for a three vane-four passage linear turbine vane cascade ...
A jet-flap blade was designed for a velocity diagram typical of the first-stage stator of a jet engi...
Design and performance of very low-solidity turbine stator blades for first stage jet engine turbine...
A semivaneless turbine stator designed to eliminate blade wakes and secondary-flow accumulations of ...
Three stator configurations were studied to determine the effect of stator outer endwall contouring ...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
An experimental and analytical investigation was conducted to determine the effect of stator endwall...
A single-stage axial-flow turbine was investigated to determine the effect of increased stator throa...
The aerodynamic performance of the inlet manifold and stator assembly of the compressor drive turbin...
This thesis describes a series of experime~taland numerical investigations into the aerodynamic perf...
An advanced laser anemometer (LA) was used to measure the axial and tangential velocity components i...
As part of the Brite/EuRam programme "Aeromechanical Design of Turbine Blades" (ADTurB) ex...
July 1981Includes bibliographical references (page 29)An experiment was carried out to examine the e...
An advanced laser anemometer (LA) was used to measure the axial and tangential velocity components i...
June 1963Also issued as: Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical E...
ABSTRACT Midspan aerodynamic measurements for a three vane-four passage linear turbine vane cascade ...
A jet-flap blade was designed for a velocity diagram typical of the first-stage stator of a jet engi...
Design and performance of very low-solidity turbine stator blades for first stage jet engine turbine...
A semivaneless turbine stator designed to eliminate blade wakes and secondary-flow accumulations of ...
Three stator configurations were studied to determine the effect of stator outer endwall contouring ...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
An experimental and analytical investigation was conducted to determine the effect of stator endwall...
A single-stage axial-flow turbine was investigated to determine the effect of increased stator throa...
The aerodynamic performance of the inlet manifold and stator assembly of the compressor drive turbin...
This thesis describes a series of experime~taland numerical investigations into the aerodynamic perf...
An advanced laser anemometer (LA) was used to measure the axial and tangential velocity components i...
As part of the Brite/EuRam programme "Aeromechanical Design of Turbine Blades" (ADTurB) ex...
July 1981Includes bibliographical references (page 29)An experiment was carried out to examine the e...
An advanced laser anemometer (LA) was used to measure the axial and tangential velocity components i...
June 1963Also issued as: Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Mechanical E...
ABSTRACT Midspan aerodynamic measurements for a three vane-four passage linear turbine vane cascade ...
A jet-flap blade was designed for a velocity diagram typical of the first-stage stator of a jet engi...
Design and performance of very low-solidity turbine stator blades for first stage jet engine turbine...