Unsteady response of an axial flow compressor to planar temperature transients

Das, Debendra K.; Peacock, R. E.

doi:10.2514/6.1982-1266

Cited by 3 publications

(3 citation statements)

References 1 publication

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“…Model predictions were validated with available experimental data of Wallner et al (1957). This model complements the modelling technique reported in (Das, et al, 1982). The • de-stabilising influences of inlet distortion as predicted by the mathematical model reported in (Baghdadi and Lucke, 1982) and Baghdadi (1982), when-applied -to several .…”

Section: Introductionsupporting

confidence: 62%

“…When the inlet is subjected to greater temperature rises beyond the limiting rate corresponding to ramp A, the surge line would be traversed by the response trajectory, and system instability would be expected to take place, Wallner et al (1957). Rudey and Antl (1970), Das, et al (1982), , and Merrington (1988). This is illustrated in Fig.…”

Section: Inlet Temperature Rampsmentioning

confidence: 99%

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Response of a Turbofan Engine Compression System to Disturbed Inlet Conditions

Abdel-Fattah

1996

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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A generic code DYNTECC has been adapted to perform a parametric study of the effect of inlet flow distortion on the stability of the Pratt and Whitney TF30 engine. This code was developed at Arnold Engineering Development Center, USA, for single and dual spool systems. It was modified at AMRL to accommodate the particular geometry of the TF30 engine. The stage characteristics needed to operate DYNTECC were derived from experimental data for the fan and low pressure compressor. For the high pressure compressor they were derived using the STGSTK code developed at NASA Lewis Research Center. This program was modified at AMRL to include real flow effects that were in turn derived using yet another adapted code CASCAD. The code was primarily used at AMRL to predict the onset of system instability due to simulated full-face rapid inlet temperature ramps typical of those caused during armament firings. It was also run with sinusoidal total pressure oscillations of varying amplitudes and frequencies at the inlet. The code predictions were compared with available data whenever possible, and were found to be consistent with the observed experimental trends.

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Section: Introductionsupporting

confidence: 62%

Section: Inlet Temperature Rampsmentioning

confidence: 99%

Response of a Turbofan Engine Compression System to Disturbed Inlet Conditions

Abdel-Fattah

1996

Volume 5: Manufacturing Materials and Metallurgy; Ceramics; Structures and Dynamics; Controls, Diagnostics and Instrumentation;

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“…Some previous investigations of inlet temperature transients into compressors mention steam ingestion as a potential cause of transients [4,5]. Analytical work dealing directly with steam ingestion effects is limited.…”

Section: Introductionmentioning

confidence: 99%

Investigation and Prediction of Steam-Induced Stall-Margin Reduction in Two Transonic Rotor Fans

Gannon

Hobson

Hedges

et al. 2014

Journal of Fluids Engineering

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An investigation into the behavior of two transonic compressor rotors operating at nearstall conditions while ingesting hot-steam was undertaken. This type of inlet flow was similar to that experienced by naval aircraft during steam catapult launches and has had the potential to adversely affect engine performance. The research was divided into three broad areas: experimental, theoretical and numerical. The first area, experimental, used the Naval Postgraduate School's transonic compressor rig. The rig was modified to introduce hot steam into the inlet flow during testing. Two rotor-only tests were completed; one with an unswept rotor and the other with a forward swept rotor. The experimental program yielded two sets of results. The first recorded data on the operational behavior of a transonic compressor ingesting a super-heated steam and air mixture, notably the quantification of the stall margin (SM) reduction. The second data set captured transient measurements of the inlet flow gas properties. The transient inlet data were then used in the second research area; a theoretical analysis based on a thermodynamic model of the inlet flow. Prior to this investigation, little information was available for higher temperature steam-air mixtures of this type. The analysis used certain simplifying assumptions to perform a fundamental of the inflow which yielded the inlet flow transient changes of specific heat capacities, gas constants, and, therefore, sonic velocities. Using these transient inlet properties, the third area of the investigation was performed, developing a numerical model. A fully transient simulation over the time period of an ingestion event would not be practical due to the large computational requirements needed. A quasi-transient method with large intermediate time steps was developed. The method is presented and was found to be reasonable at predicting the stall-margin reduction when compared to the available experimental results. These results would have potential use in design applications and for evaluating existing compressor steam ingestion tolerance.

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Education Committee Best Paper of 1996 Award: Response of a Turbofan Engine Compression System to Disturbed Inlet Conditions

Abdel-Fattah

1997

Journal of Turbomachinery

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A generic code DYNTECC has been adapted to perform a parametric study of the effect of inlet flow distortion on the stability of the Pratt and Whitney TF30 engine. This code was developed at Arnold Engineering Development Center, USA, for single and dual spool systems. It was modified at AMRL to accommodate the particular geometry of the TF30 engine. The stage characteristics needed to operate DYNTECC were derived from experimental data for the fan and low-pressure compressor. For the high-pressure compressor they were derived using the STGSTK code developed at NASA Lewis Research Center. This program was modified at AMRL to include real flow effects that were in turn derived using yet another adapted code, CASCAD. The code was primarily used at AMRL to predict the onset of system instability due to simulated full-face rapid inlet temperature ramps typical of those caused during armament firings. It was also run with sinusoidal total pressure oscillations of varying amplitudes and frequencies at the inlet. The code predictions were compared with available data whenever possible, and were found to be consistent with the observed experimental trends.

show abstract

Unsteady response of an axial flow compressor to planar temperature transients

Cited by 3 publications

References 1 publication

Response of a Turbofan Engine Compression System to Disturbed Inlet Conditions

Response of a Turbofan Engine Compression System to Disturbed Inlet Conditions

Investigation and Prediction of Steam-Induced Stall-Margin Reduction in Two Transonic Rotor Fans

Education Committee Best Paper of 1996 Award: Response of a Turbofan Engine Compression System to Disturbed Inlet Conditions

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