초록 ▼

A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially beh

A gas turbine engine is provided having an annular duct having an inner duct wall and an outer duct wall. At least one strut extends between the inner duct wall and the outer duct wall. The strut has an aerodynamic shape. At least one vane located circumferentially adjacent the strut and axially behind a leading edge of the strut, and an aerodynamic deflector located circumferentially between each strut and each vane. The aerodynamic deflector may positioned axially upstream of a flow separation point which would otherwise be caused by the strut.

대표청구항 ▼

1. A gas turbine engine comprising an annular gas path duct having an inner duct wall and an outer duct wall, the gas path duct having: a plurality of struts extending radially between the inner duct wall and the outer duct wall, the plurality of struts having an aerodynamic shape;a plurality of air

1. A gas turbine engine comprising an annular gas path duct having an inner duct wall and an outer duct wall, the gas path duct having: a plurality of struts extending radially between the inner duct wall and the outer duct wall, the plurality of struts having an aerodynamic shape;a plurality of airfoil vanes located circumferentially around the duct, the airfoil vanes extending radially between the inner duct wall and the outer duct wall, the airfoil vanes having leading edges disposed downstream of leading edges of the plurality of struts relative to a direction of gas flow through the gas turbine engine;a plurality of aerodynamic deflectors extending radially between the inner duct wall and the outer duct wall, the plurality of aerodynamic deflectors located circumferentially around the duct, a said aerodynamic deflector being circumferentially located between a said strut and an adjacent said vane; andwherein the leading edges of the plurality of struts define a first radially extending plane and the leading edges of the airfoil vanes define a second radially extending plane, and wherein leading edges of the plurality of aerodynamic deflectors are axially positioned between said first and second radially extending planes. 2. The gas turbine engine as defined in claim 1 wherein the leading edge of each said deflector is upstream of an axial point at which a flow separation substantially caused by said adjacent strut occurs when the aerodynamic deflector was not in place. 3. The gas turbine engine as defined in claim 2 wherein trailing edges of the respective struts, deflectors and vanes define a third radially extending plane. 4. The gas turbine engine as defined in claim 2 wherein trailing edges of the respective struts and deflectors define a third plane and wherein the trailing edges of the vanes define a fourth radially extending plane downstream of the third radially extending plane. 5. The gas turbine engine as defined in claim 4 wherein the second radially extending plane is disposed downstream of the third radially extending plane. 6. The gas turbine engine as defined in claim 3 wherein the trailing edges of the plurality of aerodynamic deflectors have a same shape as the trailing edges of the airfoil vanes. 7. The gas turbine engine as defined in claim 3 wherein the gas path duct defines a plurality of substantially equal throat areas between adjacent struts, deflectors and vanes, including strut-to-deflector, deflector-to-vane and vane-to-vane throat areas. 8. The gas turbine engine as defined in claim 1 wherein a said deflector positioned at a pressure side of an adjacent said strut extends further upstream than a said deflector positioned at a suction side of said adjacent strut. 9. The gas turbine engine as defined in claim 3 wherein a said deflector is positioned circumferentially mid way between adjacent a said strut and a said vane. 10. The gas turbine engine as defined in claim 1 wherein each of the struts has at least double the circumferential dimension of one of the respective vanes. 11. A vane assembly providing a section of an annular duct of a gas turbine engine for directing a fluid flow therethrough, the vane assembly comprising inner and outer duct walls, a plurality of strut fairings, aerodynamic vanes and aerodynamic deflectors each extending radially between the inner and outer duct walls, each of the strut fairings having a circumferential width dimension greater than a circumferential width dimension of the respective aerodynamic vanes, leading edges of the aerodynamic deflectors positioned upstream of leading edges of the aerodynamic vanes and downstream of leading edge of the strut fairings with respect to the fluid flow through the duct, a said aerodynamic deflector being positioned circumferentially between at least one said strut fairing and an adjacent aerodynamic vane. 12. The assembly as defined in claim 11 wherein each of the strut fairings is integrated with one of the aerodynamic vanes. 13. The assembly as defined in claim 12 wherein the leading edges of the deflectors are axially aligned with trailing edges of the aerodynamic vanes, thereby forming a plurality of vane nozzles having substantially equal throat areas. 14. The assembly as defined in claim 11 wherein the leading edge of each said deflector is upstream of an axial point at which a flow separation substantially caused by said adjacent strut fairing occurs if the deflector was not in place. 15. The assembly as defined in claim 11 wherein each of the deflectors is circumferentially positioned midway between one of the strut fairings and one of the aerodynamic vanes. 16. The assembly as defined in claim 11 wherein the deflectors comprise a first group of said deflectors, each deflector of said first group of deflectors being positioned at a pressure side of one of said strut fairings and having an aerodynamic profile in a cross-section substantially contoured to correspond with a shape of the pressure side of the strut fairing. 17. The assembly as defined in claim 11 wherein the deflectors comprise a second group of said deflectors, each deflector of said second group of deflectors being positioned at a suction side of one of said strut fairings and having an aerodynamic profile in a cross-section substantially contoured to correspond with a shape of the suction side of the strut fairing. 18. A method of channelling an axial gas flow between a strut and adjacent vane of a circumferential array of vanes in a gas turbine engine, the strut having a leading edge upstream of leading edges of the vanes with respect to the axial gas flow, the method comprising: (a) determining an axial location at which a flow separation substantially caused by the strut occurs; and(b) providing at least one deflector having an aerodynamic profile, positioned circumferentially between the strut and the adjacent one of the vanes, the deflector having a leading edge upstream of the axial point and a trailing edge downstream of the axial point, the deflector thereby extending axially through the axial location, such that in use the axial gas flow through the gas turbine engine passing the struts will be guided by the deflectors so as to substantially impede flow separation around the strut. 19. A method as defined in claim 18 wherein step (a) is conducted at both pressure and suction sides of the struts and wherein the deflector is positioned in step (b) at each of the pressure and suction sides of the strut.