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

IPC: F02C7/00 ,  F02C7/04 ,  F02K3/065 ,  F02K3/077 ,  F04D25/16 ,  F04D29/54

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

IPC: F02C7/00 ,  F02K3/077 ,  F02C7/04 ,  F02K3/065 ,  F04D25/16 ,  F04D29/54

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：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

IPC: F02C7/00 ,  F02C7/04 ,  F02K3/065 ,  F02K3/077 ,  F04D25/16 ,  F04D29/54

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).