-
Patent Agency Ranking
公开(公告)号：JP2001207911A
公开(公告)日：2001-08-03
申请号：JP2000396998
申请日：2000-12-27
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUINAN DANIEL P , HUBER DAVID J , PERKINS GARY M
Abstract: PROBLEM TO BE SOLVED: To provide a duct device capable of increasing an air flow rate passing a fan part of a gas turbine engine without increasing a diameter of a fan. SOLUTION: This duct device 10 used in the gas turbine engine 100 having two fans 102, 104 connected to a common shaft includes one primary inlet duct 12 integrated with four primary discharge ducts 14, 16, 18, 20 and two secondary inlet ducts 32, 34 integrated with one secondary discharge duct 36. Each of the ducts includes a port, the ports 38, 40 of the secondary inlet ducts 32, 34 are arranged outside in the radial direction of a port 22 of the primary inlet duct 12 and the ports 24, 26, 28, 30 of the primary discharge ducts 14, 16, 18, 20 are arranged outside in the radial direction of a port 42 of the secondary discharge duct 36.
-
公开(公告)号：DE60023093T2
公开(公告)日：2006-04-20
申请号：DE60023093
申请日：2000-12-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUINAN DANIEL P , PERKINS GARY M , HUBER DAVID J
Abstract: A ducting system for use on a gas turbine engine having two fans (102, 104) connected to a common shaft, and includes a primary inlet duct (12) that is integral with a plurality of primary discharge ducts (14, 16, 18, 20), a plurality of secondary inlet ducts (32, 34) that are integral with a secondary discharge duct (36), each of the ducts includes a port, the ports of the secondary inlet ducts (32, 34) are located radially outward of the port of the primary inlet duct (12), and the ports of the primary discharge ducts (14, 16, 18, 20) are located radially outward of the port of the secondary discharge duct (36).
-
公开(公告)号：DE69624660D1
公开(公告)日：2002-12-12
申请号：DE69624660
申请日：1996-12-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHIRLE STEVEN M , BAGHDADI SAMY , KHALID SYED J PALM BEACH GARDE , PERKINS GARY M
Abstract: The engine has an engine intake for admitting a working medium into the engine, and a fan downstream of the intake having at least one fan blade array rotatable about a central axis. There is a fan duct downstream of the fan, and a core unit also downstream of the fan and in parallel flow relationship with the fan duct, the core unit comprising, in series flow relationship. There is a guide vane array, and a hybrid stage having a rotor blade array and a stator vane array. There is a core compressor having at least one rotor blade array, the hybrid and compressor rotor blade arrays being rotatable about the central axis at a common rotational speed. There is also a fan duct bypass valve for governing flow communication between the fan and the fan duct, a compressor bypass port upstream of the compressor for selectively establishing flow communication between the core unit and the fan duct. There is a compressor bypass valve for controlling working medium flow through the bypass port. The fan duct and compressor bypass valves each have a closed position and an open position, the engine being operable in at least two modes determined by the positions of the valves such that the mass flow rate of the working medium channeled into the core unit in one of the modes exceeds that channeled into the core unit in the other of the modes.
-
公开(公告)号：DE60023093D1
公开(公告)日：2006-02-23
申请号：DE60023093
申请日：2000-12-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUINAN DANIEL P , PERKINS GARY M , HUBER DAVID J
Abstract: A ducting system for use on a gas turbine engine having two fans (102, 104) connected to a common shaft, and includes a primary inlet duct (12) that is integral with a plurality of primary discharge ducts (14, 16, 18, 20), a plurality of secondary inlet ducts (32, 34) that are integral with a secondary discharge duct (36), each of the ducts includes a port, the ports of the secondary inlet ducts (32, 34) are located radially outward of the port of the primary inlet duct (12), and the ports of the primary discharge ducts (14, 16, 18, 20) are located radially outward of the port of the secondary discharge duct (36).
-
公开(公告)号：DE69624660T2
公开(公告)日：2003-07-24
申请号：DE69624660
申请日：1996-12-06
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SCHIRLE STEVEN M , BAGHDADI SAMY , KHALID SYED J PALM BEACH GARDE , PERKINS GARY M
Abstract: The engine has an engine intake for admitting a working medium into the engine, and a fan downstream of the intake having at least one fan blade array rotatable about a central axis. There is a fan duct downstream of the fan, and a core unit also downstream of the fan and in parallel flow relationship with the fan duct, the core unit comprising, in series flow relationship. There is a guide vane array, and a hybrid stage having a rotor blade array and a stator vane array. There is a core compressor having at least one rotor blade array, the hybrid and compressor rotor blade arrays being rotatable about the central axis at a common rotational speed. There is also a fan duct bypass valve for governing flow communication between the fan and the fan duct, a compressor bypass port upstream of the compressor for selectively establishing flow communication between the core unit and the fan duct. There is a compressor bypass valve for controlling working medium flow through the bypass port. The fan duct and compressor bypass valves each have a closed position and an open position, the engine being operable in at least two modes determined by the positions of the valves such that the mass flow rate of the working medium channeled into the core unit in one of the modes exceeds that channeled into the core unit in the other of the modes.
-
-
-
-
Search Results
5
records
(took 0.023 seconds)
