Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
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Saroj Kumar Muduli
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Purna Chandra Mishra
Abstract
This paper presents the experimental results of an annular combustor. A full scale full annular combustion chamber is tested at ground test stand simulating altitude off-design operating conditions. Traversing thermocouple rakes are used to measure temperatures over the entire annulus at combustor exit. The radial temperature profile is found to be a strong function of operating parameters while the circumferential pattern factor is within the design goal. Increase in reference Mach number at these off-design conditions has caused the redial temperature profiles to deviate and increase from the intended profile. These results will be used for benchmarking the computational model. The computational model will be used for detail study of the temperature non-uniformity over the entire flight envelope and also for modification of combustor liner for performance improvement.
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Author contributions: All authors have accepted responsibility for the entire content of this manuscript and approved its submission.
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Research funding: None declared.
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Conflict of interest statement: The authors declare no conflicts of interest regarding this article.
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© 2021 Walter de Gruyter GmbH, Berlin/Boston
Artikel in diesem Heft
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
Artikel in diesem Heft
- Frontmatter
- Natural frequency analysis of a functionally graded rotor-bearing system with a slant crack subjected to thermal gradients
- Evaluation of exit pattern factors of an annular aero gas turbine combustor at altitude off-design conditions
- Research on quasi-one-dimensional modeling and performance analysis of RBCC propulsion system
- Performance characteristics of flow in annular diffuser using CFD
- Control-oriented quasi-one dimensional modeling method for scramjet
- Effect of rotor–stator rim cavity flow on the turbine
- An improved aerodynamic performance optimization method of 3-D low Reynolds number rotor blade
- Hot gas ingestion in chute rim seal clearance of gas turbine
- An improved compact propulsion system model based on batch normalize deep neural network
- Study of the vortex chamber and its application for the development of novel measurement and control devices
- Effect of equivalence ratio on the detonation noise characteristics of pulse detonation engine
- Simulation and analysis of hot plume infrared signature based on SNB model
