Abstract

The HF120 turbofan engine had achieved top-class low fuel consumption and high thrust-weight ratio in the class of engine with comparable thrust, and at the same time, shown compliance with Federal Aviation Regulations. In order to accomplish these goals, characteristic structural design requirements as typified by life-limited parts design concept have been established. HF120 parts were confirmed to meet these design requirements in compliance with Federal Aviation Regulations by applying methods including CAE optimization and enhanced structural configuration. This paper uses the fan rotor as an example of how the rotating parts in the HF120 was verified to meet design requirements and Federal Aviation Regulations through computational fluid dynamics, numerical impact analysis, frequency analysis and substantiation test. The low-pressure turbine stage1 nozzle is used here as an example of how structural parts achieved lightweight, compact and low fuel consumption.

References

1. (1) Blade containment and rotor unbalance tests, 14 Code of Federal Regulations Part 33 Amendment 30 Section 33.94
2. (2) Bird ingestion, 14 Code of Federal Regulations Part 33 Amendment 30 Section 33.76
3. (3) Vibration test, 14 Code of Federal Regulations Part 33 Amendment 30 Section 33.83

Author (organization or company)

• Junichi IKEDA（Aircraft Engine R&D Center）
• Takafumi TANAKA（Aircraft Engine R&D Center）
• Ryuji SANO（Aircraft Engine R&D Center）

Publication Information

Article of Honda R&D Technical Review Vol.26 No.2 (28 - 32)

PDF

Citation Information