Session: 40-02: Axial Compressor Instabilities and Stall

Paper Number: 151708

A System for Identifying Compressor Operating Limits in Gas Turbine Engines 

This paper introduces a novel test system capable of identifying compressor operating limits by directly testing on gas turbine engines. The system configuration is based on the fuel spiking method, which drives the compressor to the surge limit, accurately determining the compressor’s instability boundary. The method involves injecting a large amount of fuel into the combustion chamber for a short duration (up to 200 ms) while the engine is running stably. This results in a rapid increase in the post-combustion temperature (T4), raising the T4/T2 temperature ratio (where T2 is the compressor inlet temperature), and thus causing a sudden rise in the compressor discharge pressure (P3) to the point of instability without significantly increasing engine speed. The system employs a high-flow, high-pressure fuel pump, while the fuel spiking duration and flow rate are controlled by a proportional valve. Excess fuel is returned to the fuel tank via a relief valve. To validate the system, static engine tests were performed to confirm the fuel spike flow and duration with varying valve positions, ranging from 50 to 200 ms. The system enables real-time detection of compressor surge and helps to reduce test time and costs, while ensuring safe engine operation. This system was successfully used to detect surge events on a small gas turbine engine. The results demonstrate the system's effectiveness in determining compressor surge limits across a wide operating range from idle to maximum RPM, offering significant advantages in terms of cost reduction, test time, and operational safety.

Presenting Author: Anh Pham Cong Viettel Aerospace Institute, Viettel Group

Presenting Author Biography: PHAM CONG ANH

Position: MSc, Engine Design Engineer
Affiliation: Viettel Aerospace Institute, Viettel Group
Email: phamconganhxt0907@gmail.com

- Research Interests
My primary research focuses on the design and simulation of small gas turbine engines, with a particular interest in combustion chambers, aerodynamics, and testing methods. Relevant keywords include: small gas turbines, combustion chamber optimization, aerodynamics, and experimental testing methodologies.

- Education
+ Bachelor’s Degree in Gas Turbine Engines, Kharkiv Polytechnic Institute, Ukraine, 2016
+ Master’s Degree in Gas Turbine Engines, Kharkiv Polytechnic Institute, Ukraine, 2018

- Professional Experience
+ 2018–Present: Engine Design and Simulation Engineer, Viettel Aerospace Institute
+ Focus on the design, simulation, and optimization of small gas turbine engines.

- Scientific Publications and Research Achievements
+ Publications:
Lead author of "Multidisciplinary optimization of combustion chamber for small gas turbine engines" presented at the ICAS 2022 International Conference, Sweden.
Lead author of "Analysis and Optimization of Combustion Chamber for Small Gas Turbine" presented at the ACSMO International Conference, Japan.

- Technical Skills
+ Design and simulation of combustion chambers for small gas turbine engines.
+ Development of in-house software for gas turbine combustion chamber design.
+ Creation of experimental methods to determine the operational limits of compressors of gas turbine engines.
+ Simulation and calculation of aerodynamic characteristics for flying objects.

Authors:

Anh Pham Cong Viettel Aerospace Institute, Viettel Group
Hung Vu Xuan Viettel Aerospace Institute, Viettel Group
Lanh Chu Duy Viettel Aerospace Institute, Viettel Group
Minh Nguyen Phi Viettel Aerospace Institute, Viettel Group
Anh Pham Tuan Viettel Aerospace Institute, Viettel Group
Long Bui Xuan Viettel Aerospace Institute, Viettel Group
Vinh Ngo Ngoc Viettel Aerospace Institute, Viettel Group
Dung Pham Ngoc Viettel Aerospace Institute, Viettel Group