A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed t
A gas turbine engine includes a spool, a turbine coupled to drive the spool, a propulsor coupled to be rotated about an axis by the turbine through the spool, and a gear assembly coupled between the propulsor and the spool such that rotation of the turbine drives the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extend from the hub. Each of the propulsor blades has a span between a root at the hub and a tip, and a chord between a leading edge and a trailing edge. The chord forms a stagger angle α with the axis, and the stagger angle α is less than 15° at a position along the propulsor blade that is within an inboard 20% of the span.
대표청구항▼
1. A gas turbine engine comprising: a spool;a turbine coupled with said spool;a propulsor coupled to be rotated about an axis by said turbine through said spool; anda gear assembly coupled between said propulsor and said spool such that rotation of said turbine drives said propulsor at a different s
1. A gas turbine engine comprising: a spool;a turbine coupled with said spool;a propulsor coupled to be rotated about an axis by said turbine through said spool; anda gear assembly coupled between said propulsor and said spool such that rotation of said turbine drives said propulsor at a different speed than said spool,wherein said propulsor includes a hub and a row of propulsor blades that extend from said hub, each of said propulsor blades has a span between a root at said hub and a tip, and a chord between a leading edge and a trailing edge such that said chord forms a stagger angle α with said axis, and said stagger angle α is less than 15° at a position along said propulsor blade that is within an inboard 20% of said span, with said hub being at 0% of said span and said tip being at 100% of said span. 2. The gas turbine engine as recited in claim 1, wherein said stagger angle α is less than 10° at said position. 3. The gas turbine engine as recited in claim 1, wherein said stagger angle α is less than 5° at said position. 4. The gas turbine engine as recited in claim 1, wherein said chord at said position is substantially parallel to said axis. 5. The gas turbine engine as recited in claim 1, wherein said position is within 5-15% of said span. 6. The gas turbine engine as recited in claim 1, wherein said propulsor is located at an inlet of a bypass flow passage having a design pressure ratio that is between 1.1 and 1.55 with regard to an inlet pressure and an outlet pressure of said bypass flow passage. 7. The gas turbine engine as recited in claim 1, wherein said chord has a chord dimension (CD) at said tips, said row of propulsor blades defines a circumferential pitch (CP) with regard to said tips, and said row of propulsor blades has a solidity value (R) defined as CD/CP that is between 0.6 and 1.3. 8. The gas turbine engine as recited in claim 1, wherein said row of propulsor blades includes a number (N) of said propulsor blades that is no more than 20. 9. The gas turbine engine as recited in claim 1, wherein said chord has a chord dimension (CD) at said tips, said row of propulsor blades defines a circumferential pitch (CP) with regard to said tips, said row of propulsor blades has a solidity value (R) defined as CD/CP, and said row of propulsor blades includes a number (N) of said propulsor blades that is no more than 20 such that a ratio of N/R is between 8 and 28. 10. The gas turbine engine as recited in claim 1, wherein said stagger angle α varies with position of said chord along said span. 11. The gas turbine engine as recited in claim 1, wherein said stagger angle α is less than 5° at said position to reject particulate into a bypass flow passage. 12. The gas turbine engine as recited in claim 11, wherein said bypass flow passage has a bypass ratio of 18. 13. A gas turbine engine comprising: a compressor section that extends along a central axis and includes an annular splitter spaced a radial distance (D) from said central axis such that there is a core flow radially inward of said annular splitter and a bypass flow radially outward of said annular splitter; anda propulsor adjacent said compressor section, said propulsor including a hub and a row of propulsor blades that extend from said hub, each of said propulsor blades has a span between a root at said hub and a tip, and a chord between a leading edge and a trailing edge such that said chord forms a stagger angle α with said central axis, and said stagger angle α is less than 15° at a position along said propulsor blade that is radially inward of said radial distance (D). 14. The gas turbine engine as recited in claim 13, wherein said position along said propulsor blade is within an inboard 20% of said span, with said hub being at 0% of said span and said tip being at 100% of said span. 15. The gas turbine engine as recited in claim 14, wherein said position is within 5-15% of said span. 16. The gas turbine engine as recited in claim 13, including a design bypass ratio with regard to said bypass flow and said core flow that is at least 12. 17. The gas turbine engine as recited in claim 13, wherein said stagger angle α is less than 5° at said position to reject particulate into a bypass flow passage. 18. A propulsor for use in a gas turbine engine, the propulsor comprising: a rotor including a row of propulsor blades extending radially outwardly from a hub that is rotatable around an axis, each of said propulsor blades has a span between a root at said hub and a tip, and a chord between a leading edge and a trailing edge such that said chord forms a stagger angle α with said axis, and said stagger angle α is less than 15° at a position along said propulsor blade that is within an inboard 20% of said span, with said hub being at 0% of said span and said tip being at 100% of said span. 19. The propulsor as recited in claim 18, wherein said stagger angle α is less than 10° at said position. 20. The propulsor as recited in claim 18, wherein said stagger angle α is less than 5° at said position. 21. The propulsor as recited in claim 18, wherein said chord at said position is substantially parallel to said axis. 22. The propulsor as recited in claim 18, wherein said position is within 5-15% of said span. 23. The propulsor as recited in claim 18, wherein said stagger angle α is less than 5° at said position to reject particulate.
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이 특허에 인용된 특허 (7)
Wainauski Harry S. (Simsbury CT) Vaczy Carol M. (Swampscott MA), Airfoiled blade.
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