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Separated core turbofan engine; Core bunrigata turbofan engine

Technical Report:

Abstract

This report outlines the separated core turbofan engine. This engine is featured by parallel separated arrangement of a fan and core engine which are integrated into one unit in the conventional turbofan engine. In general, cruising efficiency improvement and noise reduction are achieved by low fan pressure ratio and low exhaust speed due to high bypass ratio, however, it causes various problems such as large fan and nacelle weight due to large air flow rate of a fan, and shift of an operating point affected by flight speed. The parallel separated arrangement is thus adopted. The stable operation of a fan and core engine is easily retained by independently operating air inlet unaffected by fan. The large degree of freedom of combustion control is also obtained by independent combustor. Fast response, simple structure and optimum aerodynamic design are easily achieved. This arrangement is also featured by flexibility of development and easy maintenance, and by various merits superior to conventional turbofan engines. It has no technological problems difficult to be overcome, and is also suitable for high-speed VTOL transport aircraft. 4 refs., 5 figs.
Authors:
Saito, Y; Endo, M; Matsuda, Y; Sugiyama, N; Sugahara, N; Yamamoto, K [1] 
  1. National Aerospace Laboratory, Tokyo (Japan)
Publication Date:
Apr 01, 1996
Product Type:
Technical Report
Report Number:
NAL-TR-1289
Reference Number:
SCA: 330103; 320201; PA: NEDO-96:930247; EDB-97:020521; SN: 97001728372
Resource Relation:
Other Information: PBD: Apr 1996
Subject:
33 ADVANCED PROPULSION SYSTEMS; 32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION; TURBOFAN ENGINES; CONFIGURATION; BYPASSES; BLOWERS; PROPULSION; ENERGY EFFICIENCY; NOISE POLLUTION ABATEMENT; COMPRESSION RATIO; STABILITY; DEGREES OF FREEDOM; COMBUSTION CONTROL; AERODYNAMICS; OPTIMIZATION
OSTI ID:
423552
Research Organizations:
National Aerospace Lab., Chofu, Tokyo (Japan)
Country of Origin:
Japan
Language:
Japanese
Other Identifying Numbers:
TRN: 96:930247
Availability:
Available from National Aerospace Laboratory, 44-1, Shindaiji Higashicho 7-chome, Chofu-City, Tokyo, Japan
Submitting Site:
NEDO
Size:
7 p.
Announcement Date:

Technical Report:

Citation Formats

Saito, Y, Endo, M, Matsuda, Y, Sugiyama, N, Sugahara, N, and Yamamoto, K. Separated core turbofan engine; Core bunrigata turbofan engine. Japan: N. p., 1996. Web.
Saito, Y, Endo, M, Matsuda, Y, Sugiyama, N, Sugahara, N, & Yamamoto, K. Separated core turbofan engine; Core bunrigata turbofan engine. Japan.
Saito, Y, Endo, M, Matsuda, Y, Sugiyama, N, Sugahara, N, and Yamamoto, K. 1996. "Separated core turbofan engine; Core bunrigata turbofan engine." Japan.
@misc{etde_423552,
title = {Separated core turbofan engine; Core bunrigata turbofan engine}
author = {Saito, Y, Endo, M, Matsuda, Y, Sugiyama, N, Sugahara, N, and Yamamoto, K}
abstractNote = {This report outlines the separated core turbofan engine. This engine is featured by parallel separated arrangement of a fan and core engine which are integrated into one unit in the conventional turbofan engine. In general, cruising efficiency improvement and noise reduction are achieved by low fan pressure ratio and low exhaust speed due to high bypass ratio, however, it causes various problems such as large fan and nacelle weight due to large air flow rate of a fan, and shift of an operating point affected by flight speed. The parallel separated arrangement is thus adopted. The stable operation of a fan and core engine is easily retained by independently operating air inlet unaffected by fan. The large degree of freedom of combustion control is also obtained by independent combustor. Fast response, simple structure and optimum aerodynamic design are easily achieved. This arrangement is also featured by flexibility of development and easy maintenance, and by various merits superior to conventional turbofan engines. It has no technological problems difficult to be overcome, and is also suitable for high-speed VTOL transport aircraft. 4 refs., 5 figs.}
place = {Japan}
year = {1996}
month = {Apr}
}