SELECTION OF THE RELATIVE THICKNESS OF PROFILES OF BLADES OF AN AXIAL-FLOW COMPRESSOR,
Abstract
An investigation was made to find ways for improving the strength and vibration characteristics of the shroudless blade assembly of an axial compressor. Recommendations for designing blades with an increased relative thickness of the airfoil root cross section are given. The following conclusions were reached: (a) In designing blades requiring improvements in strength, frequency characteristics, axial dimensions, and the distribution of airfoil's maximum thickness and chord along the blade must be selected in accordance with changed mechanical stresses and M number along the radius. (b) To improve the strength and vibration characteristics of blades at moderate M numbers, it is recommended that the relative thickness of the root cross section of the airfoil be increased by 15-18%, since it does not cause a significant decrease in the efficiency and pressure of the stage when the blades are made in accordance with the recommended method. (c) The increase in the blade's strength thus permits a decrease in the chord and sufficiently lowers the axial dimensions of the stage. If the initial lengthening of the blades is h < 1, stage efficiency increases. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 30, 1968
- Accession Number
- AD0685951
Entities
People
- V. V. Semov
Organizations
- National Air and Space Intelligence Center