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Sweep angle blade


sweep angle blade

an axially forward direction from.
The compressor blade of claim 16, wherein, along the length of said span, a chord, an axial center-of-gravity and a tangential center-of-gravity are defined substantially in accordance with the values of Chord, x-cg and y-cg, respectively, set forth at locations identified by span locations,.
The airfoil of claim 11, wherein a chord distribution defined by a variation in the chord of the airfoil with increasing span comprises a non-linear increasing chord distribution.The airfoil of claim 1, wherein said radially outer portion of said airfoil is located in a range of about 70 to about 100 span from said root.The airfoil of claim 3, including a transition portion between about 50 to about 70 span from said root, wherein radial sections of said airfoil have centers-of-gravity that are offset an increasing amount in an aft circumferential direction, opposite to the direction of blade rotation.A compressor blade for a gas turbine engine, said compressor blade having an airfoil comprising: laterally opposite pressure and suction sides joined together at chordally opposite leading smart money rebate and trailing edges and extending in span from a root to a tip; a radially inner portion and.The green man gaming voucher 20 airfoil of claim 11, wherein said sweep is within a range of about 10 to about 45 forward sweep along said radially outer portion,.The airfoil of claim 3, wherein a chord distribution defined by a variation in the chord of the airfoil with increasing span comprises a non-linear increasing chord distribution.
A compressor airfoil for pressurizing air yorkshire wildlife park voucher codes 2015 inside a surrounding casing, said airfoil comprising: laterally opposite pressure and suction sides joined together at chordally opposite leading and trailing edges and extending in span from a root to a tip; a radially inner portion and a radially.
The airfoil of claim 2, wherein said sweep is within a range of about 10 to about 45 forward sweep along said radially outer portion.
The airfoil of claim 11, wherein said ratio of leading edge sweep to leading edge dihedral is substantially equal to 2:1 along said radially outer portion of said airfoil.
The compressor blade of claim 18, wherein, along the length of said span, a chord, an axial center-of-gravity and a tangential center-of-gravity are defined substantially in accordance with the values of Chord, x-cg and y-cg, respectively, set forth at locations identified by span locations,.The airfoil of claim 9, wherein said forward sweep and said forward dihedral both increase monotonically along said radially outer portion of said airfoil to a location adjacent to said tip.The airfoil of claim 2, wherein said ratio of leading edge sweep to leading edge dihedral is substantially equal to 2:1 along said radially outer portion of said airfoil.The airfoil of claim 2, wherein said leading edge sweep and said leading edge dihedral both increase in a forward direction along said radially outer portion of said airfoil progressing in a radially outward direction.The airfoil of claim 14, wherein said dihedral is within a range of about 5 to about.5 forward dihedral along at least a portion of said radially outer portion.The airfoil of claim 2, wherein said dihedral is within a range of about 5 to about.5 forward dihedral along at least a portion of said radially outer portion.The berp rotor blade design.Be kept to a minimum by recognizing that the Mach number is varying along the blade so we do not have to use a constant sweep angle.The changes of the leading edge sweep angle will immediately apparent from the column headed sweep angle.The swept blade design described above is presented.The sweep angle versus dihedral angle plot for the moderate airfoil 15 M is shown as line.




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