Gas-Turbine Performance Improvements Through the Use of  Multiple Turbine Interstage Burners

Chen, Gordon; Hoffman, Matthew; Davis, Roger L.

doi:10.2514/1.2886

Cited by 14 publications

(4 citation statements)

References 7 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…Thus, the amount of cooling may actually be reduced and, in addition, we have the added benefit of reduced NOx emission because of the lowered burner temperature. Chen et al [3] included various cooling models in their investigation and concluded that the performance gains of the turbine burners were greatly reduced for aircraft engines, but significant gains still stood for ground-based engines. Their comparisons were made between engines using the same turbine inlet temperatures.…”

Section: Thermal-cycle Analysismentioning

confidence: 99%

Turbine Burners: Performance Improvement and Challenge of Flameholding

et al. 2012

View full text Add to dashboard Cite

(UCI). He received his Ph.D. degree (1985) from the University of California, Berkeley, with an emphasis in combustion science. He was a Postdoctoral Researcher at Sandia National Laboratories Combustion Research Facility until 1987, when he joined the faculty of Mechanical Engineering at UCI. Dr. Dunn-Rankin's research is primarily in combustion and energy, droplets and sprays, and applications of laser diagnostic techniques to practical engineering systems, with recent emphasis on miniature combustion systems and electrical aspects of flames. He has more than 300 technical publications and presentations in these fields, and he is a Board officer of both the International Combustion Institute and the Institute for the Dynamics of Explosions and Reactive Systems.

show abstract

Section: Thermal-cycle Analysismentioning

confidence: 99%

Turbine Burners: Performance Improvement and Challenge of Flameholding

et al. 2012

View full text Add to dashboard Cite

show abstract

“…Thus the amount of cooling may actually be reduced and in addition we have the added benefit of reduced NOx emission because of the lowered burner temperature. Chen et al [3] included various cooling models in their investigation and concluded that the performance gains of the turbine-burners were greatly reduced for aircraft engines but significant gains still stood for ground-based engines.…”

Section: Fig 4 the Specific Thrust And Specific Fuel Consumption Asmentioning

confidence: 99%

Turbine-Burner Model: Cavity Flameholding in a Converging, Turning Channel Flow

Colcord¹,

Sirignano²,

Liu³

2012

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &Amp;amp; Exhibit

View full text Add to dashboard Cite

A review of turbine-burner research and a discussion of some relevant background issues for this emerging technology are presented. The thermal cycle analysis for augmentative combustion in the passages of the turbine on a turbojet or turbofan engine is discussed, identifying the potential for dramatic improvements in engine performance. The substantial challenges of augmentative combustion integrated with the turbine function are outlined, including the need for flame stabilization in accelerating flows at the 10 5 g levels. Research findings on reacting mixing layers in accelerating flows and flameholding in high-speed flows are reviewed. Descriptions are given of various types of compact combustors which can be used as main combustors or augmentative combustors between turbine stages. An overview is given of recent computational research at UCI on the stabilization of flames in accelerating and turning flows. Two-dimensional computations for Reynolds-averaged turbulent flow through straight and turning channels are discussed. Quasi-two-dimensional representations of reacting, converging (and converging/ turning) channel flows are examined. Two-and three-dimensional computations for time-dependent transitional flows through passages are given for cases with and without cavities. Rossiter modes, found only for the non-reacting cases, are discussed. Various configurations for injection of fuel and air into the cavity are examined. Cavity placements on the inside and outside of the turn are studied to provide different centrifugal accelerations. Some indications for optimizing the cavity design are presented. Effects of the cavity length and depth, injection orientation for fuel and air into the cavity, passage turning radius, and Reynolds number magnitude are discussed. Various hydrodynamic instabilities associated with mixing and combustion in accelerating, turning flows are evaluated, and the needs for future work are identified.

show abstract

“…It had a combustor, but the gas was also burning in the turbine, of which the purpose was to realize the approximate isothermal expansion process. Because of concerns for practical application, Vogeler [13], Chen et al [14], and Bergantzel et al [15] considered one or multiple discrete reheats along the expansion section. Their studies confirmed the potential for the improvement of thrust characteristic when heating the gas in the inter-stage of turbine.…”

Section: Introductionmentioning

confidence: 99%

Performance evaluation of a novel re-cooled mixed-flow turbofan cycle for aviation power application

Sun

Wen

et al. 2020

J Therm Anal Calorim

View full text Add to dashboard Cite

A novel re-cooled mixed-flow turbofan cycle (RMTC) is proposed to meet the demand of high thrust-weight ratio for military aero-engine. Through adding a re-cooler during the compression process, the specific thrust can be improved by increasing the outer fan flow temperature and also the turbine cooling air consumption can be reduced by decreasing the inner fan flow temperature. This work conducts the modeling of ideal and actual RMTCs by using a verified original program. The effects of re-cooler location, heat transfer effectiveness, and bypass ratio on the specific thrust and fuel consumption rate are evaluated, and the RMTC performances in the entire flight envelope are discussed to estimate its applicable flight conditions. Based on the parametric analysis, locating the re-cooler after the compressor and increasing the heat transfer effectiveness are beneficial for the increase in specific thrust, while the effect of bypass ratio is related to the heat transfer capacity of recooler. The specific thrust improvement of RMTC is more significant at high flight Mach number, and hence, larger aircraft payload can be obtained with the same fuel mass. The assessment results show that the proposed RMTC system exhibits potential application for high-speed military aircraft.

show abstract

Gas-Turbine Performance Improvements Through the Use of Multiple Turbine Interstage Burners

Cited by 14 publications

References 7 publications

Turbine Burners: Performance Improvement and Challenge of Flameholding

Turbine Burners: Performance Improvement and Challenge of Flameholding

Turbine-Burner Model: Cavity Flameholding in a Converging, Turning Channel Flow

Performance evaluation of a novel re-cooled mixed-flow turbofan cycle for aviation power application

Contact Info

Product

Resources

About