초록 ▼

A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils de

A turbofan includes a row of fan blades extending from a supporting disk inside an annular casing. Each blade includes an airfoil having opposite pressure and suction sides extending radially in span between a root and tip and axially in chord between leading and trailing edges. Adjacent airfoils define corresponding flow passages therebetween for pressurizing air. Each airfoil includes stagger increasing between the root and tip, and the flow passage has a mouth between the airfoil leading edge and the suction side of an adjacent airfoil and converges to a throat aft from the mouth. The row includes no more than twenty fan blades having low tip solidity for increasing the width of the passage throat.

대표청구항 ▼

The invention claimed is: 1. A fan for a gas turbine engine comprising: an annular casing; a disk disposed coaxially inside said casing and including a row of fan blades extending radially outwardly from a perimeter rim thereof; each of said blades including an airfoil having circumferentially oppo

The invention claimed is: 1. A fan for a gas turbine engine comprising: an annular casing; a disk disposed coaxially inside said casing and including a row of fan blades extending radially outwardly from a perimeter rim thereof; each of said blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between opposite leading and trailing edges, with said airfoils defining corresponding flow passages therebetween for pressurizing air; each of said airfoils including stagger increasing between said root and said tip to position the leading edge of one airfoil circumferentially adjacent to the suction side of the next adjacent airfoil to define a mouth for said flow passage therebetween, with said flow passage converging to a throat aft from said mouth; and said row including no more than twenty and no less than eighteen of said fan blades having a solidity defined by the ratio of said airfoil chord over the circumferential pitch and being low in magnitude at said tips and no greater than about 1.2 and greater than about 1.0 to position the leading edge of each tip circumferentially near the trailing edge of the next adjacent tip. 2. A fan according to claim 1 wherein: said airfoil stagger positions the trailing edge of one airfoil circumferentially adjacent to the pressure side of the next adjacent airfoil to define an outlet for said flow passage therebetween; and said airfoil tips vary in width between said leading and trailing edges to converge said flow passage from said mouth to said throat and diverge said flow passage from said throat to said outlet. 3. A fan according to claim 2 wherein said airfoils include forward aerodynamic sweep at said tips thereof. 4. A fan according to claim 3 wherein said converging-diverging flow passages at said airfoil tips are sized and configured for receiving supersonic flow of said air at said leading edges, followed by shock therein, and with subsonic diffusion aft from said throat. 5. A fan according to claim 4 wherein said tip solidity includes the ratio of chord over diameter having a value to provide a circumferential gap between said leading and trailing edges of adjacent tips. 6. A fan according to claim 5 further comprising: a smooth annular tip shroud mounted inside said casing and surrounding said airfoil tips, and positioned closely adjacent thereto to define a correspondingly small tip clearance therewith; and a row of outlet guide vanes extending radially inwardly from said casing and spaced aft from said blade row, and being more than twice in number than said fan blades for reducing noise from said fan. 7. A fan according to claim 6 wherein: said blade row includes only twenty fan blades; and adjacent airfoils have said circumferential gap near said tips, followed radially inwardly by circumferential overlap therebetween, and further followed radially inwardly by a circumferential gap near said roots. 8. A fan according to claim 7 wherein said solidity at said tips is about 1.17. 9. A fan according to claim 6 wherein: said blade row includes only eighteen fan blades; and said circumferential gap between adjacent airfoils extends from root to tip thereof. 10. A fan according to claim 9 wherein said solidity at said tips is about 1.05. 11. A fan for a gas turbine engine comprising: an annular casing; a disk disposed coaxially inside said casing and including a row of fan blades extending radially outwardly from a perimeter rim thereof; each of said blades including an airfoil having circumferentially opposite pressure and suction sides extending radially in span from a root to a tip, and extending axially in chord between opposite leading and trailing edges, with said airfoils defining corresponding flow passages therebetween for pressurizing air; each of said airfoils including stagger increasing between said root and said tip to position the leading edge of one airfoil circumferentially adjacent to the suction side of the next adjacent airfoil to define a mouth for said flow passage therebetween, with said flow passage converging to a throat aft from said mouth; and said row including no more than twenty of said fan blades having a solidity defined by the ratio of said airfoil chord over the circumferential pitch and being low in magnitude at said tips to position the leading edge of each tip circumferentially near the trailing edge of the next adjacent tip and correspondingly increase the width of said throat. 12. A fan according to claim 11 wherein said tip solidity is low in magnitude to provide a circumferential gap between said leading and trailing edges of adjacent tips. 13. A fan according to claim 12 wherein: said airfoil stagger positions the trailing edge of one airfoil circumferentially adjacent to the pressure side of the next adjacent airfoil to define an outlet for said flow passage therebetween; and said airfoil tips vary in width between said leading and trailing edges to diverge said flow passage therebetween. 14. A fan according to claim 13 wherein said airfoils include forward aerodynamic sweep at said tips thereof. 15. A fan according to claim 14 further comprising: a smooth annular tip shroud mounted inside said casing and surrounding said airfoil tips, and positioned closely adjacent thereto to define a correspondingly small tip clearance therewith; and a row of outlet guide vanes extending radially inwardly from said casing and spaced aft from said blade row, and being more than twice in number than said fan blades for reducing noise from said fan. 16. A fan according to claim 15 wherein said airfoil tips have an axially arcuate contour, and said tip shroud has a complementary axially arcuate contour for maintaining a substantially uniform tip clearance radially therebetween and axially between said leading and trailing edges. 17. A fan according to claim 14 wherein: said solidity includes the ratio of chord over diameter; and said blade row includes only twenty or only eighteen fan blades, and said chord to diameter ratio at said tips is the same in both species. 18. A fan according to claim 14 wherein said blade row includes twenty or eighteen blades, and said solidity at said tips thereof is greater than about 1.0 and no greater than about 1.2. 19. A fan according to claim 14 wherein said blades are sized and configured for pressurizing said air under an aerodynamic loading having a value of at least about 0.29 and defined by the ratio of the specific enthalpy rise across said airfoils over the square of velocity of said tips. 20. A fan according to claim 14 wherein said diverging flow passages at said airfoil tips are sized and configured for receiving supersonic flow of said air at said leading edges, followed by shock therein, and with subsonic diffusion aft of said throat. 21. A fan according to claim 14 wherein: said blade row includes only twenty fan blades; and adjacent airfoils have said circumferential gap near said tips, followed radially inwardly by circumferential overlap therebetween, and further followed radially inwardly by a circumferential gap near said roots. 22. A fan according to claim 21 wherein said solidity at said tips is about 1.17. 23. A fan according to claim 14 wherein: said blade row includes only eighteen fan blades; and said circumferential gap between adjacent airfoils extends from root to tip thereof. 24. A fan according to claim 23 wherein said solidity at said tips is about 1.05. 25. A fan according to claim 14 wherein said airfoil tips vary in width between said leading and trailing edges to converge said flow passage from said mouth to said throat and diverge said flow passage from said throat to said outlet. 26. A method of using said fan according to claim 14 comprising: powering said fan in a turbofan engine for propelling an aircraft in flight; rotating said airfoil tips for achieving supersonic flow of said air at said leading edges thereof; and aerodynamically loading said airfoils to propel said aircraft at cruise with increased efficiency due to low solidity while maintaining stability and stall margin of said fan. 27. A method of improving aerodynamic efficiency in said engine according to claim 11 comprising: deriving said fan from a pre-existing fan design by reducing said solidity at said airfoil tips while maintaining substantially equal the ratio of tip chord over tip diameter of said derived fan and said pre-existing fan; and increasing area of said flow passages at said throats thereof. 28. A method according to claim 27 further comprising increasing camber of said airfoils at said tips thereof.