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An axial-flow gas turbine engine includes a plurality of inlet guide vanes (V) which are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct) of a turbine. The inner peripheral wall (Ch) of the gas passage includes inner peripher

An axial-flow gas turbine engine includes a plurality of inlet guide vanes (V) which are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct) of a turbine. The inner peripheral wall (Ch) of the gas passage includes inner peripheral concave portions (Cc1 and Cc3) on an upstream side, and inner peripheral convex portions (Cv1 and Cv3) on a downstream side. The outer peripheral wall (Ct) of the gas passage includes outer peripheral convex portions (Cv2 and Cv4) on an upstream side, and outer peripheral concave portions (Cc2 and Cc4) on a downstream side. Therefore, a pressure difference in a radial direction of the inlet guide vane V is reduced or partially reversed, and a secondary flow toward an inner side in the radial direction can be suppressed to reduce pressure loss.

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1. A shape of a gas passage in an axial-flow gas turbine engine in which a plurality of inlet guide vanes (V) are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct), comprising: said inner peripheral wall (Ch) between a leading

1. A shape of a gas passage in an axial-flow gas turbine engine in which a plurality of inlet guide vanes (V) are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct), comprising: said inner peripheral wall (Ch) between a leading edge (LE) and a trailing edge (TE) of the inlet guide vane (V) comprises: an inner peripheral concave portion (Cc1) curved into a concave shape in a radial direction on an upstream side of a fluid flow direction; andan inner peripheral convex portion (Cv1) curved into a convex shape in the radial direction on a downstream side of the fluid flow direction; andsaid inner peripheral convex portion (Cv1) is positioned on the outer side in the radial direction with respect to a reference line connecting inner ends in the radial direction of the leading edge (LE) and the trailing edge (TE) of the inlet guide vane (V);wherein each of said plurality of inlet guide vanes (V) includes a chord length in an axial direction that is larger relative to a span length in the radial direction with the leading edge being inclined to the upstream side at a tip side, outer side in the radial direction, as compared to the hub side, inner side in the radial direction. 2. The shape of a gas passage in an axial-flow gas turbine engine according to claim 1, wherein the inner peripheral wall (Ch) has three inflection points. 3. The shape of a gas passage in an axial-flow gas turbine engine according to claim 2, wherein the inner peripheral wall (Ch) has one inflection point in a range from the leading edge (LE) to a 50% chord position, and has two inflection points in a range from the 50% chord position to the trailing edge (TE). 4. A shape of a gas passage in an axial-flow gas turbine engine in which a plurality of inlet guide vanes (V) are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct), comprising: said outer peripheral wall (Ct) between a leading edge (LE) and a trailing edge (TE) of the inlet guide vane (V) comprises: an outer peripheral convex portion (Cv2) curved into a convex shape in a radial direction on an upstream side of a fluid flow direction; andan outer peripheral concave portion (Cc2) curved into a concave shape in the radial direction on a downstream side of the fluid flow direction);wherein each of said plurality of inlet guide vanes (V) includes a chord length in an axial direction that is larger relative to a span length in the radial direction with the leading edge being inclined to the upstream side at a tip side, outer side in the radial direction, as compared to the hub side, inner side in the radial direction. 5. The shape of a gas passage in an axial-flow gas turbine engine according to claim 4, wherein the inner peripheral wall (Ch) has three inflection points. 6. The shape of a gas passage in an axial-flow gas turbine engine according to claim 5, wherein the inner peripheral wall (Ch) has one inflection point in a range from the leading edge (LE) to a 50% chord position, and has two inflection points in a range from the 50% chord position to the trailing edge (TE). 7. The shape of a gas passage in an axial-flow gas turbine engine according to claim 4, wherein the outer peripheral wall (Ct) has three or more inflection points. 8. The shape of a gas passage in an axial-flow gas turbine engine according to claim 7, wherein the outer peripheral wall (Ct) has two inflection points in a range from the leading edge (LE) to a 50% chord position, and has one or more inflection points in a range from the 50% chord position to the trailing edge (TE). 9. A shape of a gas passage in an axial-flow gas turbine engine in which a plurality of inlet guide vanes (V) are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct), comprising: said inner peripheral wall (Ch) between a leading edge (LE) and a trailing edge (TE) of the inlet guide vane (V) comprises: an inner peripheral concave portion (Cc3) curved into a concave shape in a radial direction on an upstream side of a fluid flow direction; andan inner peripheral convex portion (Cv3) curved into a convex shape in the radial direction on a downstream side of the fluid flow direction;said inner peripheral convex portion (Cv3) is positioned on the outer side in the radial direction with respect to a reference line connecting inner ends in the radial direction of the leading edge (LE) and the trailing edge (TE) of the inlet guide vane (V); andsaid outer peripheral wall (Ct) between the leading edge (LE) and the trailing edge (TE) of the inlet guide vane (V) comprises: an outer peripheral convex portion (Cv4) curved into a convex shape in a radial direction on an upstream side of the fluid flow direction; andan outer peripheral concave portion (Cc4) curved into a concave shape in the radial direction on a downstream side of the fluid flow direction);wherein each of said plurality of inlet guide vanes (V) includes a chord length in an axial direction that is larger relative to a span length in the radial direction with the leading edge being inclined to the upstream side at a tip side, outer side in the radial direction, as compared to the hub side, inner side in the radial direction. 10. The shape of a gas passage in an axial-flow gas turbine engine according to claim 9, wherein the inner peripheral wall (Ch) has three inflection points. 11. The shape of a gas passage in an axial-flow gas turbine engine according to claim 10, wherein the inner peripheral wall (Ch) has one inflection point in a range from the leading edge (LE) to a 50% chord position, and has two inflection points in a range from the 50% chord position to the trailing edge (TE). 12. The shape of a gas passage in an axial-flow gas turbine engine according to claim 9, wherein the outer peripheral wall (Ct) has three or more inflection points. 13. The shape of a gas passage in an axial-flow gas turbine engine according to claim 12, wherein the outer peripheral wall (Ct) has two inflection points in a range from the leading edge (LE) to a 50% chord position, and has one or more inflection points in a range from the 50% chord position to the trailing edge (TE). 14. A shape of a gas passage in an axial-flow gas turbine engine in which a plurality of inlet guide vanes (V) are radially disposed in an annular gas passage defined between an inner peripheral wall (Ch) and an outer peripheral wall (Ct), comprising: a height in a radial direction of the gas passage between the inner peripheral wall (Ch) and the outer peripheral wall (Ct) has at least one maximum value, and has at least one minimum value on a downstream side in a fluid flow direction from a position of the maximum value);wherein each of said plurality of inlet guide vanes (V) includes a chord length in an axial direction that is larger relative to a span length in the radial direction with the leading edge being inclined to an upstream side at a tip side, outer side in the radial direction, as compared to the hub side, inner side in the radial direction. 15. The shape of a gas passage in an axial-flow gas turbine engine according to claim 14, wherein the outer peripheral wall (Ct) between a leading edge (LE) and a trailing edge (TE) of the inlet guide vane (V) comprises: an outer peripheral convex portion (Cv2) curved into a convex shape in a radial direction on an upstream side in the fluid flow direction; and an outer peripheral concave portion (Cc2) curved into a concave shape in the radial direction on a downstream side of the fluid flow direction, anda minimum value, which is different from the at least one minimum value, occurs in the outer peripheral convex portion (Cv2).