Author: Laurence J. HeidelbergPublisher:
ISBN:
Category : Optical instruments
Languages : en
Pages : 28
Book Description
Effect of Reynolds Number on Overall Performance of a 3.7-inch-diameter Six-stage Axial-flow Compressor
Author: Laurence J. HeidelbergPublisher:
ISBN:
Category : Optical instruments
Languages : en
Pages : 28
Book Description
Effect of Reynolds Number on Overall Performance of a 6-inch Radial Bladed Centrifugal Compressor
Author: Laurence J. HeidelbergPublisher:
ISBN:
Category : Astronautics and civilization
Languages : en
Pages : 36
Book Description
Investigation of Reynolds Number Effect on Performance of an Eight-stage Axial-flow Research Compressor with Long- and Medium-chord Lengths in the Two Transonic Inlet Stages
Author: Gilbert K. SieversPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 21
Book Description
The chords of the first two stages of an eight-stage axial-flow compressor with two transonic inlet stages were doubled, and the effects of Reynolds number on the over-all performance were investigated and compared with those of the original compressor.
Effect of Reynolds Number on Overall Performance of a 6-inch Radial Bladed Centrifugal Compressor
Author: Laurence J. HeidelbergPublisher:
ISBN:
Category : Aerospace engineering
Languages : en
Pages : 24
Book Description
"Overall performance is presented over a range of compressor inlet pressures from a nominal 1.5 to 8.6 psia (l.0xl04 to 5.9x104 N/m2 abs) and corresponding Reynolds number range of 0.32X106 to 1.8X106. As inlet pressure and thus Reynolds number was decreased, a progressive degradation in efficiency along with a lowering of the surge and maximum flow points was observed. These changes in performance are explained in terms of changing viscous losses and changing effective flow areas with Reynolds number. A comparison between the data and the commonly used 0.2 power of Reynolds number relation to loss is made".--P. [i].
Applied Mechanics Reviews
Author: Some Effects of Blade Trailing-edge Thickness on Performance of a Single-stage Axial-flow Compressor
Author: J. J. MosesPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 18
Book Description
Investigation of Effects of Reynolds Number on Large Double-entry Centrifugal Compressor
Author: Karl KovachPublisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 30
Book Description
Scientific and Technical Aerospace Reports
Author: Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 748
Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
Investigation of Effects of Reynolds Number on Over-all Performance of an Eight-stage Axial-flow Research Compressor with Two Transonic Inlet Stages
Author: Richard P. GeyeThe Influence of the Diameter Ratio on the Characteristics Diagram of the Axial Compressor
Author: Bruno EckertPublisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 632
Book Description
With the further development of axial blowers into highly loaded flow machines, the influence of the diameter ratio upon air output and efficiency gains in significance. Clarification of this matter is important for single-stage axial compressors, and is of still greater importance for multistage ones, and particularly for aircraft power plants. Tests with a single-stage axial blower gave a decrease in the attainable maximum pressure coefficient and optimum efficiency as the diameter ratio increased. The decrease must be ascribed chiefly to the guide surface of the hub and housing between the blades increasing with the diameter ratio.