Abstract An axial-flow transsonic compressor wherein a flow path is defined by a housing of the compressor and an inlet bladed stator, at least one transsonic stage and at least one subsonic stage, arranged within the housing in succession along the path of the flow of the fluid being compressed. The transsonic stage includes a transsonic rotor and a bladed stator. The subsonic stage includes a rotor and a stator. Each blade of the inlet stator structure has an angle of setting of a profile of a peripheral section perpendicular to a blade axis determined with respect to a vector of the circumferential speed of the transsonic rotor in excess of 90°; an angle of setting of a profile of a radially innermost or sleeve section perpendicular to the blade axis determined with respect to the vector of the circumferential speed of the transsonic rotor below 90° and an angle of setting of a profile of a middle section perpendicular to the blade axis determined with respect to the vector of the circumferential speed of the transsonic rotor substantially equalling 90°. The curvature of the middle line of a profile of the middle section equals zero. Each blade of the stator structure of the transsonic stage has a chord value increasing from a sleeve section profile toward a peripheral section profile.
An axial flow transsonic compressor comprising: a compressor housing; an inlet bladed stator structure; at least one transsonic compression stage and at least one subsonic compression stage; said inlet bladed stator structure, said transsonic compression stage and said subsonic compression stage being arranged within said compressor housing, in succession along the flow path of the compressed fluid through said compressor and defining the flow section thereof, said transsonic stage comprising a transsonic rotor and a bladed stator structure, said bladed stator structure being mounted downstream along the path of the compressed fluid from said transsonic rotor, said subsonic stage comprising a subsonic rotor and a stator structure; said inlet bladed stator structure comprising blades each having a peripheral section perpendicular to the blade axis, a radially innermost section perpendicular to the blade axis and a middle section perpendicular to the blade axis, the angle of setting of a profile of said peripheral section, determined with respect to a vector of the circumferential speed of said transsonic rotor being in excess of 90°, the angle of setting of a profile of said radially innermost section determined with respect to the vector of the circumferential speed of said transsonic rotor being less than 90°, and the angle of setting of a profile of said middle section, determined with respect to the vector of the circumferential speed of said transsonic rotor substantially equalling 90°, said profile of said middle section having a middle line with a curvature equalling zero, said stator structure of said transsonic stage comprising blades each having a radially innermost section and a peripheral section, and having a chord increasing in value from a profile of said radially innermost section toward a profile of said peripheral section.
Claim 2
Dependent Claim
287 words
An axial flow transsonic compressor comprising: a compressor housing; an inlet bladed stator structure; at least one transsonic compression stage and at least one subsonic compression stage; said inlet bladed stator structure, said transsonic compression stage and said subsonic compression stage being arranged within said compressor housing, in succession along the flow path of the compressed fluid through said compressor and defining the flow section thereof, said transsonic stage comprising a transsonic rotor and a bladed stator structure, said bladed stator structure being mounted downstream along the path of the compressed fluid from said transsonic rotor, said subsonic stage comprising a subsonic rotor and a stator structure; said inlet bladed stator structure comprising blades each having a peripheral section perpendicular to the blade axis, a radially innermost section perpendicular to the blade axis and a middle section perpendicular to the blade axis, the angle of setting of a profile of said peripheral section, determined with respect to a vector of the circumferential speed of said transsonic rotor being in excess of 90°, the angle of setting of a profile of said radially innermost section determined with respect to the vector of the circumferential speed of said transsonic rotor being less than 90°, and the angle of setting of a profile of said middle section, determined with respect to the vector of the circumferential speed of said transsonic rotor substantially equalling 90°, said profile of said middle section having a middle line with a curvature equalling zero, said stator structure of said transsonic stage comprising blades each having a radially innermost section and a peripheral section, and having a chord increasing in value from a profile of said radially innermost section toward a profile of said peripheral section.
Claim 3
Dependent Claim
36 words
An axial-flow compressor as set forth in claim 1, wherein said profile of the middle section of said blade of said inlet stator structure has equal radii of curvature of the inlet and outlet edges thereof.