Blading system for axial compressors with axially opposing base merged double triangular prism device blades

3:

• The blade structure of claim 2, wherein used as non-rotating blades or stator blades (54,53,63,12,46) with different lengths to reduce the hub solidity of the flow path of transonic/conventional axial flow compressors.

4:

• The blade structure of claim 2, wherein used as rotating or rotor blades (22,64,52,48,44,58) with optimized length of the blade at the throat section of the flow path volume and minimum length of the blade at the leading and trailing edges. This design reduces tonal nodes, tip leakages, pressure losses, corner drags, horseshoe vortices, and adverse pressure gradients, resulting in improved efficiency and performance in a transonic/conventional axial flow compressor.

5:

• The Blade structure, as described in claim 1 incorporating with an additional feature as
• The cross-sectional diamond airfoils of the blades vary in proportion between the two opposing imaginary triangles of the diamond airfoil and its total size varies for different radial locations from the hub to the tip. This variation is attributed to the radial velocity gradient, which is decreasing from the tip to the hub for a rotor (63,31) and vice versa for a stator (64,18). This specialized configuration results in an amplified acceleration of the magnitude of velocity without changing the vector associated, promoting uniformity across radial locations from the hub to the tip. Consequently, the adoption of this blade structure significantly reduces the necessity for high differential stagger angles throughout the radial locations by bringing a flow uniformity over different radial locations.

6:

• The blade structure as described in claim 2, claim 3 and claim 4 incorporating with additional features like
• for the defined continuous blade structure which have a geometry of an axially opposed based merged double triangular prisms (63,64), the cross-sectional diamond airfoils of these defined continuous blade structures, the proportion between the two opposing imaginary triangles of the diamond airfoil and its total size varies for different radial locations from the hub to the tip (31,18). This variation is attributed to the radial velocity gradient, which is decreasing from the tip to the hub for a rotor (64) and vice versa for a stator (63). This is due to the high requirement of flow acceleration at the hub and low demand at the tip of the blade structure. This specialized configuration results in an amplified acceleration of the magnitude of velocity without changing the vector associated, promoting uniformity across radial locations from the hub to the tip. Consequently, the adoption of this blade structure significantly reduces the necessity for high differential stagger angles throughout the radial locations by bringing a flow uniformity over different radial locations.

7:

• The hub and tip walls of both the rotors and stators sections are designed with an initial positive slope extending to a minimum throat cross-sectional area, followed by a negative slope after the minimum throat, resulting in a horizontal converging-diverging flow path between the rotor blades and stator blades (44,46,50,51,49,10,29,19) This specific configuration is intended to minimize energy losses and facilitate wake dilution, allowing for total energy recovery through the effective straining over incoming wakes at the high-velocity field of the throat. The utilization of converging-diverging flow paths enhances the overall efficiency of the system.

8:

• The blade structure as described in claim 3 employs a key and hole configuration (54,56,57). This configuration is defined by the perfect fit of the tip of the stator blade (56) over the hub surface (57), which is achieved through a void formed by a positive slope, followed by a minimum length point, and then a negative slope on the stator blade tips (56) and an overage formed due to vice versa over the hub surface (57). This meticulous arrangement ensures a secure attachment of stator blades to the hub surface (56,57). The designed configuration not only enhances resistance to vibrations but also effectively dampens effects during blade fluttering, thereby contributing to increased reliability in axial flow compressors and gas turbine jet engines.

9:

• A converging-diverging flow process achieved by placing the blade structures (38,59,39) defined in claim 1, claim 2, claim 3, claim 4, claim 5, claim 6, claim 8 and the flow path described in claim 7 (50,51), which is to reduce flow losses and to enhance the total pressure output in a flow in between the Compressor rotor and stator blades by featuring
• the convergence of the flow which accelerates the flow to a maximum velocity gradient at the throat (65) of the consecutively placed blades, moreover, for a near sonic flow entry, a cross combination of Prandtl-Meyer expansion wave forms at this location (65). This process accelerates the low momentum fluids and it forms a strong velocity field (65) which imposes strains over the incoming wakes of the flow results in a well-structured total pressure recovery. in addition to that, for a supersonic flow entry, this process will weaken the strength of the leading-edge shockwaves (38), further reduces the flow distortion, disturbances, turbulences and energy losses.
• then the flow converges to form the delayed oblique shock waves in cross arrangement (39,40) in between the diamond blades.