Evaluation of a Mixed Flow Turbofan Engine with Intermediate Turbine Burning for a Supersonic Aircraft

Bergantzel, Michael; Waters, Mark

doi:10.4271/2007-01-3932

Cited by 2 publications

(5 citation statements)

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“…Subsequently, the operating points of HPT stage 2 (HPT2) and HPT stage 1 (HPT1) can be determined by moving upstream: the NDMF at the HPT2 outlet (7) must equal the NDMF at (8). Thus, the characteristic curves of HPT2 determine the NDMF at the HPT2 inlet (6), which equals the NDMF at the HPT1 outlet (5). As long as the nozzle is choked, i.e.…”

Section: Case 1: No Itr -mentioning

confidence: 99%

“…the operating point at (8) is on the straight section of the curve, the expansion ratio of each turbine stage is fixed. Figure 2 -Expansion section maps without reheat CASE 2: ITR -In the case reheat is introduced between HPT1 and HPT2, this causes a total temperature increase from station (5) to (6) as it is shown in Figure 3. Thereby, reheat alters the NDMF conservation.…”

Section: Case 1: No Itr -mentioning

confidence: 99%

“…Starting from a switched-off second burner (i.e. SBTR = 1), the progressive addition of heat in the reheat combustor causes an increase in the SBTR and in the difference between the NDMF at points (5) and (6). This is graphically represented by the vertical distance between the dashed red lines in Figure 3.…”

Section: Equationmentioning

confidence: 99%

“…al. [4] and Bergantzel and Waters [5]. Their results show a potential for significant performance improvements, when introducing a second burner.…”

Section: Introductionmentioning

confidence: 98%

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On the performance simulation of inter-stage turbine reheat

Pellegrini

Nikolaidis

Pachidis

et al. 2017

Applied Thermal Engineering

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Several authors have suggested the implementation of reheat in high ByPass Ratio (BPR) aero engines, to improve engine performance. In contrast to military afterburning, civil aero engines would aim at reducing Specific Fuel Consumption (SFC) by introducing 'Inter-stage Turbine Reheat' (ITR). To maximise benefits, the second combustor should be placed at an early stage of the expansion process, e.g. between the first and second High-Pressure Turbine (HPT) stages. The aforementioned cycle design requires the accurate simulation of two or more turbine stages on the same shaft. The Design Point (DP) performance can be easily evaluated by defining a Turbine Work Split (TWS) ratio between the turbine stages. However, the performance simulation of Off-Design (OD) operating points requires the calculation of the TWS parameter for every OD step, by taking into account the thermodynamic behaviour of each turbine stage, represented by their respective maps. No analytical solution of the aforementioned problem is currently available in the public domain. This paper presents an analytical methodology by which ITR can be simulated at DP and OD. Results show excellent agreement with a commercial, closed-source performance code; discrepancies range from 0% to 3.48%, and are ascribed to the different gas models implemented in the codes. Highlights  An innovative gas turbine performance simulation methodology is proposed  It allows to perform DP and OD performance calculations for complex engines layouts  It is essential for inter-turbine reheat (ITR) engine performance calculation  A detailed description is provided for fast and flexible implementation  The methodology is successfully verified against a commercial closed-source software

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Section: Case 1: No Itr -mentioning

confidence: 99%

Section: Case 1: No Itr -mentioning

confidence: 99%

Section: Equationmentioning

confidence: 99%

“…al. [4] and Bergantzel and Waters [5]. Their results show a potential for significant performance improvements, when introducing a second burner.…”

Section: Introductionmentioning

confidence: 98%

See 2 more Smart Citations

On the performance simulation of inter-stage turbine reheat

Pellegrini

Nikolaidis

Pachidis

et al. 2017

Applied Thermal Engineering

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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

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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.

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Evaluation of a Mixed Flow Turbofan Engine with Intermediate Turbine Burning for a Supersonic Aircraft

Cited by 2 publications

References 0 publications

On the performance simulation of inter-stage turbine reheat

On the performance simulation of inter-stage turbine reheat

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

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