Aerodynamic performance of a ceramic-coated core turbine vane tested with cold air in a two-dimensional cascade /

Experimental results of varying the blade-shroud clearance in a 6.02-inch radial-inflow turbine /

Futral, Samuel M.
Holeski, Donald E.

Prepared at Lewis Research Center."January 1970."Cover title.Includes bibliographical references (p....

An adverse effect of film cooling on the suction surface of a turbine vane /

Gladden, Herbert J.
Gauntner, James W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode of...

Experimental studies on the aerodynamic performance and dynamic response of flow direction sensing vanes /

Barna, P.S.
Crossman, Gary R., joint author.
United States. National Aeronautics and Space Administration.
Langley Research Center.
Old Dominion University.

January 1976

Cover title.Includes bibliographical references (p. 26-27).Mode of access: Internet

Research turbine for high-temperature core engine application /

Szanca, Edward M.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references.1. Cold-air overal...

A cascade investigation of a convection- and film-cooled turbine vane made from radially stacked laminates /

Gladden, Herbert J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode of...

Metal temperatures and coolant flow in a wire-cloth transpiration-cooled turbine vane /

Gladden, Herbert J.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode of...

Pressure-loss and flow coefficients inside a chordwise-finned, impingement, convection, and film air-cooled turbine vane /

Hippensteele, Steven A.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Effects of a ceramic coating on metal temperatures of an air-cooled turbine vane /

Gladden, Herbert J.
Liebert, Curt H.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"Lewis Research Center."February 1980"--Cover.Includes bibliographical references.Mode of access: In...

Gas turbine ceramic-coated-vane concept with convection-cooled porus metal core /

Kascak, Albert F.
Lewis Research Center.
Propulsion Laboratory (U.S.)
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"December 1981"--Cover.STAR Category 07."Propulsion Laboratory.""Lewis Research Center.""AVRADCOM Re...

Flow measurement in base cooling air passages of a rotating turbine blade /

Liebert, Curt H.
Pollack, Frank G.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 /

Schum, Harold J.
Nunamaker, Robert R.
Petrash, Donald A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 27).Mode of access: Internet

Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine /

Whitney, Warren J.
Behning, Frank P.
Schum, Harold J.
Lewis Research Center.

Prepared at Lewis Research Center.Cover title.Includes bibliographical references.1. Turbine design ...

Incidence loss for a core turbine rotor blade in a two-dimensional cascade /

Stabe, Roy G.
Kline, John F.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 9).Mode of acc...

Cold-air performance of a 12.766-centimeter-tip aixial-flow cooled turbine /

Haas, Jeffrey E.
Kofskey, Milton G., joint author.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1977

Issued Sept. 1977.Includes bibliographical references.3. Effect or rotor tip clearance on overall pe...

Cold-air investigation of 4 1/2-stage turbine with stage-loading factor of 4.66 and high specific work output : II - stage group performance /

Whitney, Warren J.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"June 1980"--Cover."Lewis Research Center."Includes bibliographical references.Mode of access: Inter...

Experimental results of varying the blade-shroud clearance in a 6.02-inch radial-inflow turbine /

Futral, Samuel M.
Holeski, Donald E.

Prepared at Lewis Research Center."January 1970."Cover title.Includes bibliographical references (p....

An adverse effect of film cooling on the suction surface of a turbine vane /

Gladden, Herbert J.
Gauntner, James W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode of...

Experimental studies on the aerodynamic performance and dynamic response of flow direction sensing vanes /

Barna, P.S.
Crossman, Gary R., joint author.
United States. National Aeronautics and Space Administration.
Langley Research Center.
Old Dominion University.

January 1976

Cover title.Includes bibliographical references (p. 26-27).Mode of access: Internet

Research turbine for high-temperature core engine application /

Szanca, Edward M.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references.1. Cold-air overal...

A cascade investigation of a convection- and film-cooled turbine vane made from radially stacked laminates /

Gladden, Herbert J.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode of...

Metal temperatures and coolant flow in a wire-cloth transpiration-cooled turbine vane /

Gladden, Herbert J.

January 1975

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 10-11).Mode of...

Pressure-loss and flow coefficients inside a chordwise-finned, impingement, convection, and film air-cooled turbine vane /

Hippensteele, Steven A.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Effects of a ceramic coating on metal temperatures of an air-cooled turbine vane /

Gladden, Herbert J.
Liebert, Curt H.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"Lewis Research Center."February 1980"--Cover.Includes bibliographical references.Mode of access: In...

Gas turbine ceramic-coated-vane concept with convection-cooled porus metal core /

Kascak, Albert F.
Lewis Research Center.
Propulsion Laboratory (U.S.)
United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.

January 1981

"December 1981"--Cover.STAR Category 07."Propulsion Laboratory.""Lewis Research Center.""AVRADCOM Re...

Flow measurement in base cooling air passages of a rotating turbine blade /

Liebert, Curt H.
Pollack, Frank G.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 17).Mode of ac...

Experimental investigation of two-stage air-cooled turbine suitable for flight at Mach 2.5 /

Schum, Harold J.
Nunamaker, Robert R.
Petrash, Donald A.
Lewis Research Center.
United States. National Aeronautics and Space Administration.

January 1959

"November 1959."Cover title.Includes bibliographical references (p. 27).Mode of access: Internet

Cold-air investigation of a 3 1/2-stage fan-drive turbine with a stage loading factor of 4 designed for an integral lift engine /

Whitney, Warren J.
Behning, Frank P.
Schum, Harold J.
Lewis Research Center.

Prepared at Lewis Research Center.Cover title.Includes bibliographical references.1. Turbine design ...

Incidence loss for a core turbine rotor blade in a two-dimensional cascade /

Stabe, Roy G.
Kline, John F.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 9).Mode of acc...

Cold-air performance of a 12.766-centimeter-tip aixial-flow cooled turbine /

Haas, Jeffrey E.
Kofskey, Milton G., joint author.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1977

Issued Sept. 1977.Includes bibliographical references.3. Effect or rotor tip clearance on overall pe...

Cold-air investigation of 4 1/2-stage turbine with stage-loading factor of 4.66 and high specific work output : II - stage group performance /

Whitney, Warren J.
Lewis Research Center.
United States. National Aeronautics and Space Administration. Scientific and Technical Information Office.

January 1980

"June 1980"--Cover."Lewis Research Center."Includes bibliographical references.Mode of access: Inter...

Experimental results of varying the blade-shroud clearance in a 6.02-inch radial-inflow turbine /

Futral, Samuel M.
Holeski, Donald E.

Prepared at Lewis Research Center."January 1970."Cover title.Includes bibliographical references (p....

An adverse effect of film cooling on the suction surface of a turbine vane /

Gladden, Herbert J.
Gauntner, James W.
Lewis Research Center.

January 1974

Prepared at Lewis Research Center.Cover title.Includes bibliographical references (p. 12-13).Mode of...

Experimental studies on the aerodynamic performance and dynamic response of flow direction sensing vanes /

Barna, P.S.
Crossman, Gary R., joint author.
United States. National Aeronautics and Space Administration.
Langley Research Center.
Old Dominion University.

January 1976

Cover title.Includes bibliographical references (p. 26-27).Mode of access: Internet

Aerodynamic performance of a ceramic-coated core turbine vane tested with cold air in a two-dimensional cascade /

Abstract

Extracted data

Aerodynamic performance of a ceramic-coated core turbine vane tested with cold air in a two-dimensional cascade /

Abstract

Extracted data

Related items

Related items