Patent application number | Description | Published |
20090148282 | 3D CONTOURED VANE ENDWALL FOR VARIABLE AREA TURBINE VANE ARRANGEMENT - A turbine section of a gas turbine engine includes an arcuate vane platform segment having a substantially flat surface over which a rotational turbine vane may swing. | 06-11-2009 |
20090191045 | LOW PRESSURE TURBINE WITH COUNTER-ROTATING DRIVES FOR SINGLE SPOOL - A low pressure turbine for a gas turbine engine includes inner and outer counter-rotating rotor sets, with both said rotor sets driving a common shaft. | 07-30-2009 |
20100209238 | TURBINE VANE AIRFOIL WITH TURNING FLOW AND AXIAL/CIRCUMFERENTIAL TRAILING EDGE CONFIGURATION - An airfoil with turning flow comprises a first surface, a second surface, a leading edge and a trailing edge. The first and second surfaces extend from the leading edge to a trailing edge. A chord extends from a midpoint of the leading edge to a midpoint of the trailing edge, defining a duct angle of at least fifteen degrees with respect to a turbine axis. An axial length of the chord defines an aspect ratio of at most one with respect to an average radial span of the leading and trailing edges. In a region of the trailing edge, an axial angle is at most four degrees and a circumferential angle is at most ten degrees, where the circumferential angle is defined in a direction opposite the turning flow. | 08-19-2010 |
20120070297 | AFT LOADED AIRFOIL - An example airfoil array includes an airfoil array configured to rotate within a turbomachine at a different rotational speed than a fan within the turbomachine. The airfoil array includes a first airfoil that is circumferentially spaced a distance from an adjacent second airfoil. A ratio of the distance to an axial chord length of the first airfoil is less than 1.3. An uncovered turning angle of the first airfoil is greater than 15 degrees. | 03-22-2012 |
20120291449 | Turbine Section of High Bypass Turbofan - A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170. | 11-22-2012 |
20130223983 | COUNTER ROTATING LOW PRESSURE TURBINE WITH SPLITTER GEAR SYSTEM - A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades. | 08-29-2013 |
20140102076 | Turbine Section of High Bypass Turbofan - A turbofan engine has an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio ratio is below about 170. | 04-17-2014 |
20140174055 | TURBINE SECTION OF HIGH BYPASS TURBOFAN - A turbofan engine is disclosed and includes a fan and a compressor in communication with the fan section, a combustor, a turbine and a speed reduction mechanism coupled to the fan and rotatable by the turbine. The turbine includes a first turbine section that includes three or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to a bypass area is less than about 170. | 06-26-2014 |
20140202133 | GAS TURBINE ENGINE MID TURBINE FRAME WITH FLOW TURNING FEATURES - A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°. | 07-24-2014 |