Patent application number | Description | Published |
20130340406 | FAN STAGGER ANGLE FOR GEARED GAS TURBINE ENGINE - A gas turbine engine includes a spool, a turbine coupled with 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 spool results in rotation of the propulsor at a different speed than the spool. The propulsor includes a hub and a row of propulsor blades that extends 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 such that the chord forms a stagger angle α with the axis. The stagger angle α is less than 62° at all positions along the span, with said hub being at 0% of the span and the tip being at 100% of the span. | 12-26-2013 |
20150233251 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope crosses an initial axial stacking offset that corresponds to the 0% span position at a zero-crossing position. A first axial stacking offset X | 08-20-2015 |
20150233252 | GAS TURBINE ENGINE AIRFOIL - An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starting at the 0% span position is either zero or positive. The first critical point is in the range of 5-15% span. | 08-20-2015 |
20150233323 | GAS TURBINE ENGINE AIRFOIL - A gas turbine engine includes a fan section, a compressor section and a turbine section, one of which includes an airfoil. The airfoil includes pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a maximum chord length projection that is not in an axial view. | 08-20-2015 |
20150354362 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm). | 12-10-2015 |
20150354363 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve corresponding to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position. The trailing edge sweep angle is positive from 0% span to at least 95% span. | 12-10-2015 |
20150354364 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a curve that corresponds to a relationship between a trailing edge sweep angle and a span position. The trailing edge sweep angle is in a range of 10° to 20° in a range of 40-70% span position, and the trailing edge sweep angle is positive from 0% span to at least 95% span. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. | 12-10-2015 |
20150354367 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes an airfoil having pressure and suction sides extending in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. | 12-10-2015 |
20150361797 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans aftward and the negative slope leans forward relative to an engine axis. The positive slope crosses an initial axial stacking offset corresponding to the 0% span position at a zero-crossing position. A first axial stacking offset X | 12-17-2015 |
20160024929 | GAS TURBINE ENGINE AIRFOIL - An airfoil for a turbine engine includes an airfoil that has pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a leading edge dihedral and a span position. The leading edge dihedral is negative from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning, and a negative dihedral corresponds to pressure side-leaning. The airfoil is a fan blade for a gas turbine engine. The airfoil has a relationship between a trailing edge dihedral and a span position. The trailing edge dihedral is positive from the 0% span position to the 100% span position. A positive dihedral corresponds to suction side-leaning and a negative dihedral corresponds to pressure side-leaning. | 01-28-2016 |
20160032728 | GAS TURBINE ENGINE AIRFOIL - An airfoil of a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a tangential stacking offset and a span position that is at least a third order polynomial curve that includes at least one positive and negative slope. The positive slope leans toward the suction side and the negative slope leans toward the pressure side. An initial slope starts at the 0% span position is either zero or positive. The first critical point is less than 15% span. | 02-04-2016 |
Patent application number | Description | Published |
20080258398 | SEAL - The technology of the present application provides seal to be engaged between a fitting and a port to prevent leaking of media passing through the fitting and port. The seal includes upper and lower protruding portions that are compressible and deformable to provide higher sealing forces and an air tight seal at standard industry torque and compression load values. | 10-23-2008 |
20090243219 | HIGH TEMPERATURE DYNAMIC SEAL - A high temperature dynamic seal and methods of assembly and use are presented. In one embodiment, the dynamic seal is provided as a rotating seal, which includes a stationary ring and rotating ring assembly, with a seal ring that is positioned between the stationary ring member and the rotating ring assembly. In some embodiments, one or more high temperature seals create a seal between the stationary ring member and a device in which the dynamic seal is used. Similarly one or more high temperature seals create a seal between the rotating ring assembly and a rotating shaft of the device. In one aspect, one or more of the high temperature seals are formed from a metallic material with various cross-sectional shapes. | 10-01-2009 |
20120061922 | Annular Sealing Device - An annular seal comprising a metallic ring having a cross section. The cross section includes an axially extending body portion having a radial width and an axial height. A spaced apart pair of sealing arms extend axially from the body portion, wherein each sealing arm includes a radially opposed arcuate sealing surface. The arcuate sealing surface may be convex, for example. The spaced apart pair of sealing arms are spaced apart a radial distance greater than the radial width of the body portion. A sealing system comprises a plurality of interconnected metallic rings wherein the body portion engages the sealing arms of an adjacent metallic ring. | 03-15-2012 |
20150159755 | JACKETED RESILIENT METAL SEAL - A resilient metal seal that includes a PTFE jacket or liner capable of improving the sealing performance of the resilient metal seal and providing a near chemically inert surface to protect the seal from coming into contact with potentially damaging media is provided. In some embodiments, the resilient metal seal is an E-, U-, C-, or V-shaped resilient metal seal. A jacket made of PTFE or similar material can be included on the interior or exterior surface of the resilient metal seal. The jacket can include a locking feature to prevent against the jacket becoming dislodged from the resilient metal seal. | 06-11-2015 |