Add to ORKGA methodology based on geometric construction of CDA profiles and CFD flow simulation has been used to design a stator blade of a 3-stage LP compressor. The designed CDA blade is shown to13; perform better in terms of efficiency, pressure ratio and stall margin of the compressor compared to the original MCA blade
The basic tool set to design multi-stage axial compressors consists of fast codes for throughflow an...
This research determines the relationship between the High-Pressure Compressor (HPC) rotor blade des...
Pratt & Whitney Aircraft is conducting a test program for NASA in order to demonstrate that a contro...
A methodology based on geometric construction of CDA profiles and CFD flow simulation has been used ...
With an aim to improve the performance of a multistage LP compressor, one of the stator blades has b...
This paper describes the design and performance evaluation of a controlled diffusion aerofoil (CDA) ...
A second generation, highly loaded stator having controlled diffusion airfoil (CDA) sections with en...
The objective of the presented work is to perform numerical and experimental studies on compressor s...
International Gas Turbine Conference and Exhibit; 8-12 Jun. 1986; Dusseldorf; GermanyThe mid-span se...
The purpose of this research was to develop a searchable, expandable database of compressor blade pr...
This thesis contains a detailed investigation of second-generation controlled-diffusion compressor s...
Ensuring a high degree of commonality among a range of products can dramatically decrease developmen...
Aircraft are incontestably an important way of transportation in our society, for both commercial an...
International audienceThis paper describes a new design method for high Reynolds number subsonic com...
The pursuit of efficient, compact and lightweight aircraft engines are important as it leads to a re...
The basic tool set to design multi-stage axial compressors consists of fast codes for throughflow an...
This research determines the relationship between the High-Pressure Compressor (HPC) rotor blade des...
Pratt & Whitney Aircraft is conducting a test program for NASA in order to demonstrate that a contro...
A methodology based on geometric construction of CDA profiles and CFD flow simulation has been used ...
With an aim to improve the performance of a multistage LP compressor, one of the stator blades has b...
This paper describes the design and performance evaluation of a controlled diffusion aerofoil (CDA) ...
A second generation, highly loaded stator having controlled diffusion airfoil (CDA) sections with en...
The objective of the presented work is to perform numerical and experimental studies on compressor s...
International Gas Turbine Conference and Exhibit; 8-12 Jun. 1986; Dusseldorf; GermanyThe mid-span se...
The purpose of this research was to develop a searchable, expandable database of compressor blade pr...
This thesis contains a detailed investigation of second-generation controlled-diffusion compressor s...
Ensuring a high degree of commonality among a range of products can dramatically decrease developmen...
Aircraft are incontestably an important way of transportation in our society, for both commercial an...
International audienceThis paper describes a new design method for high Reynolds number subsonic com...
The pursuit of efficient, compact and lightweight aircraft engines are important as it leads to a re...
The basic tool set to design multi-stage axial compressors consists of fast codes for throughflow an...
This research determines the relationship between the High-Pressure Compressor (HPC) rotor blade des...
Pratt & Whitney Aircraft is conducting a test program for NASA in order to demonstrate that a contro...