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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.
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公开(公告)号：FR2837877A1
公开(公告)日：2003-10-03
申请号：FR0303491
申请日：2003-03-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SILLENCE MARK A , GUINAN DANIEL P , NEMECEK DENNIS J , SALVADOR COSTANTE , WEBSTER HENRY K , FORTIN THOMAS B , RINELLA SERGIO , NIGAM RAVI K
Abstract: The present invention relates to a scram jet engine for use with a hypersonic vehicle. The scram jet engine has an upper boundary wall, a lower boundary wall, and a plurality of side walls defining an inner air flowpath. The walls are formed by a plurality of tubular heat exchanger panels. Each of the heat exchanger panels comprises a plurality of structural panels, each having a plurality of cooling passages, joined together. In the scram jet engine of the present invention, fuel may be used as a coolant and supplied to the cooling passage.
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公开(公告)号：FR2845423A1
公开(公告)日：2004-04-09
申请号：FR0311505
申请日：2003-10-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUINAN DANIEL P , DRAKE ALAN , ANDREADIS DEAN , BECKEL STEPHEN A
Abstract: The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading edge and the leading edges of the sidewalls intersect the leading edge of the cowl flap.
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Patent Agency Ranking
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).
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公开(公告)号：FR2845423B1
公开(公告)日：2008-08-22
申请号：FR0311505
申请日：2003-10-01
Applicant: UNITED TECHNOLOGIES CORP
Inventor： GUINAN DANIEL P , DRAKE ALAN , ANDREADIS DEAN , BECKEL STEPHEN A
Abstract: The present invention relates to an improved variable geometry inlet for a scram jet engine having at least one combustor module. The variable geometry inlet comprises each combustor module having two sidewalls. Each of the sidewalls has a central portion with a thickness and a tapered profile forward of the central portion. The tapered profile terminates in a sharp leading edge. The variable geometry inlet further comprises each module having a lower wall and a movable cowl flap positioned forward of the lower wall. The movable cowl flap has a leading edge and the leading edges of the sidewalls intersect the leading edge of the cowl flap.
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公开(公告)号：FR2837877B1
公开(公告)日：2006-06-09
申请号：FR0303491
申请日：2003-03-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SILLENCE MARK A , GUINAN DANIEL P , NEMECEK DENNIS J , SALVADOR COSTANTE , WEBSTER HENRY K , FORTIN THOMAS B , RINELLA SERGIO , NIGAM RAVI K
Abstract: The present invention relates to a scram jet engine for use with a hypersonic vehicle. The scram jet engine has an upper boundary wall, a lower boundary wall, and a plurality of side walls defining an inner air flowpath. The walls are formed by a plurality of tubular heat exchanger panels. Each of the heat exchanger panels comprises a plurality of structural panels, each having a plurality of cooling passages, joined together. In the scram jet engine of the present invention, fuel may be used as a coolant and supplied to the cooling passage.
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公开(公告)号：FR2878579A1
公开(公告)日：2006-06-02
申请号：FR0510665
申请日：2005-10-19
Applicant: UNITED TECHNOLOGIES CORP
Inventor： DRAKE ALAN , GUINAN DANIEL P
Abstract: Aéronef (10), selon un premier aspect de l'invention, ayant un statoréacteur, à combustion supersonique, comprenant un trajet d'écoulement variant dans trois dimensions. Selon un second aspect de l'invention, un procédé pour lancer un aéronef (10) ayant un statoréacteur à combustion supersonique avec une section de tuyère (32) et un propulseur d'appoint à propergol solide (40) positionné dans la section de tuyère (32) est fourni. Le procédé comprend les étapes : d'allumer le propulseur (10) d'appoint à propergol solide (40) pour accélérer l'aéronef (10) jusqu'à une vitesse où le statoréacteur à combustion supersonique peut fonctionner ; de dégager la section de tuyère (32) par l'éjection du propulseur d'appoint à propergol solide (40) de la section de tuyère (32) ; d'injecter du carburant dans un écoulement d'air passant par le statoréacteur à combustion supersonique ; et d'allumer le carburant et l'air pour fournir une poussée à l'aéronef (10).
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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).
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