Abstract
An improved integrated afterburner scheme was proposed to solve the problem of too large mass of traditional afterburner and too significant flow loss in non-augmentation condition. This scheme canceled the conventional stabilizer of blunt body, and a sudden expanding structure of central cone for stabilizing the flame was adopted. Numerical simulation was conducted to research its performance. The result indicates that the scheme is not sensitive to inlet parameters; total pressure recovery coefficients of three schemes on all cases are greater than 0.96; afterburner efficiency is close to 0.90; the scheme with lobed mixer has the best overall performance.
| Original language | English |
|---|---|
| Pages (from-to) | 1119-1124 |
| Number of pages | 6 |
| Journal | Hangkong Dongli Xuebao/Journal of Aerospace Power |
| Volume | 30 |
| Issue number | 5 |
| DOIs | |
| State | Published - 1 May 2015 |
Keywords
- Afterburner
- Combustion efficiency
- Integrated
- Lobed mixer
- Overall performance
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