Experimental study on characteristic calibration of separated exhaust system

LI Qiufeng; LI Mi; GAO Xiang; WANG Dingqi

doi:10.11729/syltlx20220056

Volume 37 Issue 6

Dec. 2023

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Journal of Experiments in Fluid Mechanics > 2023 > 37(6): 61-69. > DOI: 10.11729/syltlx20220056

LI Q F, LI M, GAO X, et al. Experimental study on characteristic calibration of separated exhaust system[J]. Journal of Experiments in Fluid Mechanics, 2023, 37(6): 61-69. DOI: 10.11729/syltlx20220056

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Experimental study on characteristic calibration of separated exhaust system

Chinese Flight Test Establishment, Xi'an　710089, China

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Received Date: June 26, 2022
Revised Date: October 11, 2022
Accepted Date: October 18, 2022
Available Online: December 05, 2022

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Abstract

Abstract

In flight testing, the aeroengine flight thrust is indirectly obtained by the gas generator method. In order to improve the calculation accuracy of the flight thrust, it is necessary to accurately obtain the characteristics of the exhaust system. The laboratory calibration test and numerical simulation research were carried out by using the large bypass ratio separated exhaust system scale model. The results show that: the core nozzle characteristics obtained by the two methods are consistent, and the values are close. When the maximum core nozzle pressure ratio is 1.44, the deviations of the mass flow and the thrust are 0.73% and 0.18%, respectively; the characteristics of the separated exhaust system obtained by the two methods have the same trend and close values. When the max bypass nozzle pressure ratio equals 1.46, the deviations of the mass flow and the thrust are 0.64% and 0.18%, respectively; when the physical model and geometric model of the large bypass ratio separated exhaust system are reasonably simplified, the characteristic deviations of the separated exhaust system obtained by the two methods are in good agreement.
- exhaust system,
- nozzle characteristic,
- calibration,
- large bypass ratio

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