Patent application number | Description | Published |
20090000265 | Gas Turbines with Multiple Gas Flow Paths - An representative gas turbine includes: a first annular gas flow path; a second annular gas flow path located radially outwardly from the first gas flow path; in series order, a multi-stage fan, radially inboard portions of a first set of high pressure compressor blades, a second set of high pressure compressor blades, a combustion section and a high pressure turbine, positioned along the first gas flow path; and in series order, the multi-stage fan and radially outboard portions of the first set of high pressure compressor blades, positioned along the second gas flow path such that the inboard portions of the first set of high pressure compressor blades, the second set of high pressure compressor blades, the combustion section and the high pressure turbine are not positioned along the second gas flow path. | 01-01-2009 |
20090000270 | Gas Turbines with Multiple Gas Flow Paths - A representative gas turbine includes: a high pressure spool; a high pressure compressor; a high pressure turbine mechanically coupled to the high pressure spool; a lower pressure spool; a lower pressure turbine mechanically coupled to the lower pressure spool; a fan having a first set of fan blades and a second set of fan blades, the second set of fan blades being located downstream of the first set of fan blades and being operative to rotate at a rotational speed corresponding to a rotational speed of the lower pressure spool; and a gear assembly mechanically coupled to the lower pressure spool and engaging the first set of fan blades such that rotation of the lower pressure spool rotates the first set of fan blades at a lower rotational speed than the rotational speed of the second set of fan blades. | 01-01-2009 |
20090000271 | Gas Turbines with Multiple Gas Flow Paths - Gas turbines with multiple gas flow paths are provided. In this regard, a representative gas turbine includes: a spool; a compressor; a turbine mechanically coupled to the spool; the compressor having a first set of blades and a second set of blades, the second set of blades being located downstream of the first set of blades, the first set of blades and the second set of blades being driven by the spool; and means for enabling the first set of blades to rotate at a lower rotational speed than the second set of blades. | 01-01-2009 |
20090092480 | GAS TURBINE ENGINE HAVING CORE AUXILIARY DUCT PASSAGE - A gas turbine engine system includes a nacelle assembly, a core engine and a mixer disposed between the nacelle assembly and the core engine. The core engine includes a core passage and a core auxiliary duct passage. The core auxiliary duct passage includes an inlet for receiving a portion of a core airflow form the core engine and an outlet for discharging a portion of the core airflow received from the core engine. | 04-09-2009 |
20110056208 | REVERSED-FLOW CORE FOR A TURBOFAN WITH A FAN DRIVE GEAR SYSTEM - A gas turbine engine comprises a fan drive gear system, a low spool connected to the fan drive gear system, and a high spool disposed aft of the low spool. The low spool comprises a rearward-flow low pressure compressor disposed aft of the fan drive gear system, and a forward-flow low pressure turbine disposed aft of the low pressure compressor. The high spool comprises a forward-flow high pressure turbine disposed aft of the low pressure turbine, a combustor disposed aft of the high pressure turbine, and a forward-flow high pressure compressor disposed aft of the combustor. | 03-10-2011 |
20120023961 | GAS TURBINE ENGINE HAVING CORE AUXILIARY DUCT PASSAGE - A method of controlling a gas turbine engine having a core engine including a core passage and an auxiliary duct passage includes sensing an operability condition, and diverting a portion of a core airflow through the auxiliary duct passage in response to sensing the operability condition. | 02-02-2012 |
20120304660 | TURBOMACHINE COMBUSTORS HAVING DIFFERENT FLOW PATHS - An example turbomachine assembly includes a first combustor configured to combust fuel and compressed air and a second combustor configured to combust fuel and compressed air. Flow moves through the first combustor in a first direction and flow moves though the second combustor in a second direction different than the first direction. The first combustor is axially spaced from the second combustor. | 12-06-2012 |
20130000323 | DIFFERENTIAL GEAR SYSTEM WITH CARRIER DRIVE - A differential gear system for a gas turbine engine includes an assembly of a ring gear, a sun gear, and a plurality of planet gears, and a planet carrier. The plurality of planet gears are enmeshed between the ring gear and the sun gear. The planet carrier acts as an input to rotatably drive the planet gears, the sun gear, and ring gear of the gas turbine engine. | 01-03-2013 |
20130025286 | GAS TURBINE ENGINE WITH AFT CORE DRIVEN FAN SECTION - A gas turbine engine includes a low spool along an engine axis with a forward fan section and a low pressure turbine section. A high spool along the engine axis with a high pressure turbine section and an aft core driven fan section (CDFS), the aft core driven fan section (CDFS) axially aft of the high pressure turbine section along the engine axis. | 01-31-2013 |
20130098050 | GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION - A gas turbine engine includes a fan section and an intercooling turbine section along an engine axis aft of a fan section and forward of a combustor section. | 04-25-2013 |
20130098055 | GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION AND INTERCOOLING TURBINE SECTION BYPASS - A gas turbine engine includes an intercooling turbine section to at least partially drive one of a low spool and a high spool. An intercooling turbine section bypass to selectively bypass at least a portion of a core flow through an intercooling turbine section bypass path around the intercooling turbine section. | 04-25-2013 |
20130104521 | GAS TURBINE ENGINE WITH TWO-SPOOL FAN AND VARIABLE VANE TURBINE | 05-02-2013 |
20130104522 | GAS TURBINE ENGINE WITH VARIABLE PITCH FIRST STAGE FAN SECTION | 05-02-2013 |
20130104523 | GAS TURBINE ENGINE WITH AUXILIARY FAN | 05-02-2013 |
20130104524 | TURBOFAN WITH GEAR-DRIVEN COMPRESSOR AND FAN-DRIVEN CORE | 05-02-2013 |
20130104560 | GAS TURBINE ENGINE WITH INTERCOOLING TURBINE SECTION | 05-02-2013 |
20130121824 | GAS TURBINE ENGINE HAVING CORE AUXILIARY DUCT PASSAGE - A gas turbine engine system according to an exemplary aspect of the present disclosure includes, among other things, a nacelle assembly defined about an axis and a core engine positioned radially inward of the nacelle assembly and having a core passage and at least one core auxiliary duct passage. The at least one core auxiliary duct passage includes an inlet for receiving a portion of a core airflow from the core engine and an outlet for discharging the portion of the core airflow. At least one of the inlet and the outlet are selectively translatable to divert the portion of the core airflow into the at least one core auxiliary duct passage and a mixer disposed between the nacelle assembly and the core engine. | 05-16-2013 |
20130145769 | Gas Turbine Engine with Variable Overall Pressure Ratio - A gas turbine engine has a variable overall pressure rate (“OPR”). The engine includes a high pressure compressor having at least a primary stage having a set of primary rotors and a secondary stage having a set of secondary rotors. A clutch is provided to selectively engage the secondary rotors with the primary rotors. Engagement of the clutch may be controlled based on the vehicle travel mode, such as disengaging during a takeoff mode to reduce turbine entry temperature and engaging during a loiter mode to increase OPR. | 06-13-2013 |
20140271121 | GAS TURBINE ENGINE ARCHITECTURE WITH INTERCOOLED TWIN CENTRIFUGAL COMPRESSOR - A gas turbine engine includes an intercooled twin centrifugal compressor. A pipe diffuser extends from the intercooled twin centrifugal compressor into an airflow path. | 09-18-2014 |