文章信息/Info

Title:

Study on Flame Resistance of Carbon Fiber/Resin Composites

文章編號:

1674-3962(2025)10-0938-07

作者:

李敏; 李林; 李松陽; 何歆; 冀浩

1. 中國航發商用航空發動機有限責任公司，上海 200241 2. 中國民用航空局第二研究所，四川 成都 610041 3. 中國民用航空適航審定中心，北京 100102

Author(s):

LI Min;  LI Lin;  LI Songyang;  HE Xin;  JI Hao

1. AECC Commercial Aircraft Engine Co��, Ltd��, Shanghai 200241, China 2. The Second Research Institute of Civil Aviation Administration of China,Chengdu 610041, China 3. Airworthiness Certification Center, Civil Aviation Administration of China,Beijing 100102,China

關鍵詞:

碳纖維/樹脂復合材料; 防火實驗; 火焰耐受性; 溫度; 適航

Keywords:

carbon fiber/resin composites;  fire test;  flame resistance;  temperature; airworthiness

分類號:

TB334;V258;V244.1+2

DOI:

10.7502/j.issn.1674-3962.202409002

文獻標志碼:

A

摘要:

碳纖維/樹脂復合材料由于比強度高、可設計性強的優點在民用航空發動機上有著越來越重要的應用。當復合材料部件的功能為發動機防火墻時，需要開展設計評估，表明其對航空發動機適航規定（CCAR-33R2）第33-17條防火條款的適航符合性。為解決現階段復合材料部件缺乏火焰包容能力的實驗研究和基礎實驗數據支撐的問題，開展了不同層厚的熱固型復合材料（碳纖維/環氧樹脂）和熱塑型復合材料（碳纖維/聚醚醚酮）防火實驗。防火實驗結果表明，經過15 min標準火焰沖擊，2種復合材料均未出現燒穿現象，展現出良好的火焰包容能力。通過對實驗件表面溫度的測量，建立了其火焰耐受性隨層厚增加的變化規律。對比分析了2種復合材料的背火面溫度差異及影響因素，這對復合材料部件防火適航設計與驗證、提高發動機防火安全性具有指導意義。

Abstract:

Carbon fiber/resin composites play an increasingly critical role in civil aviation engines. When composite components work as firewalls, a design assessment is required to demonstrate airworthiness compliance with Airworthiness Standards: Aircraft Engines(CCAR-33R2) 33-17 fire protection. To address the issue that lacking of tests study on fire-resistance of composites components and accumulate fundamental experimental data for fire protection design of composites in civilian aero-engine, the thickness-dependent flame resistance of thermosetting composites (carbon fiber/epoxy resin) and thermoplastic composites (carbon fiber/polyether ether ketone) was investigated by fire tests. Fire tests results show that both composites did not burn through after impingement of standard flame for 15 minutes, demonstrating good flame containment capacity. By measuring the temperature on the backward side, the changes in flame resistance with increasing layer thickness were revealed. A comparative analysis was conducted on the temperature difference on the backward face between the two composites and the influencing factors, which gives significant guidance for the aeronautical certification and validation of fire safety designs for composites, as well as for enhancing the overall fire safety of engines.