Axial compressor guide vanes

摘要

The invention relates to gas turbine engine and may be used in axial compressors of gas turbine engines. The guide vane of an axial compressor comprising fixed in the housing outer rim is rigidly connected with the rotor spacer mounted coaxially rim to form a flow channel, and the blade fixedly connected base with an outer rim disposed radially in the flow channel and having a pen with the height of the blade varying profile cross sections formed symmetrically with respect to the midline of the cross section of the pen and formed by the inlet and outlet edges of the pen, made in the form of a toroidal surface stey conjugate between a lateral aerodynamic surfaces of the vacuum and pressure, wherein the blade axis is curved in the meridional plane and in the circumferential direction and intersect at one of the end transverse sections pen link-blade axis extending radially through the center of the middle line of the same cross-sectional pen. The inventive blade axis intersects the layout axis in the cross section of the blade base, and the circumferential coordinate points of the median lines of the cross sectional profile of the pen is defined by the following equation: Y (x _a, z _a) = [Ω ₁ (x _a, z _a) ± Ω ₂ (z _o)] × z ₁ wherein Y (x _a, z _o) - the circumferential coordinate of the middle line calculated cross-sectional profiles;₁ Ω (x _a, z _o) - relative circumferential coordinate of the middle line profiles pen base, is equal to zero at x = _about 0.5; Ω ₂ (z _o) - relative displacement in the circumferential direction of the pen core profiles; Z ₁ - the height of the blade on the layout axis; z _on - the relative coordinate in height blade;_xo - relative axial coordinate midline basic profiles, defined by the ratio _of x = (x-X ₁₎ / (X ₂ -X ₁₎ where x - coordinate of the current point midline basic profiles of the blade; X ₁ - axial coordinate of the middle line of basic profiles pen on the blade inlet; X ₂ - axial coordinate of the middle line of the pen base profiles on the blade outlet, wherein the relative displacement in the circumferential direction of the pen base profiles is defined as: where: d - factor chosen in the range from -0.01 to 0.01; C ₁ - constant chosen in the range 0-0.4; C ₂ - constant chosen in the range 0,09-1,19; C ₃ - a constant chosen in the range from -0.58 to 0.58.