Combined Pressure and Temperature Distortion Effects on Internal Flow of a Turbofan Engine

Braithwaite, W. M.; Soeder, Ronald H.

doi:10.2514/3.57927

Cited by 12 publications

(6 citation statements)

References 2 publications

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“…ω is the mass density of the membrane. For silicon material, E = 190 GPa, μ = 0.278, ω = 2.33 g/cm 3 . Figs.…”

Section: Acoustic Sensing Principlementioning

confidence: 99%

“…The acoustic characteristics of aeroengine are high sound pressure level (SPL), and the maximum SPL of Boeing for the fuselage array application sensor can be as high as 172 dB [2]. In addition, both inlet pressure and temperature distortion will affect the aeroengine stability and its power output [3], thus the simultaneous measurement of the two parameters are useful. The present acoustic technology utilized in aeroacoustic fuselage is piezoresistive pressure transducer, which has disadvantage of power consumption associated with biasing of piezoresistors, difficulty in expand array scale and vulnerable to electromagnetic interference.…”

Section: Introductionmentioning

confidence: 99%

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A Compact Fiber Optic Fabry–Perot Sensor for Simultaneous Measurement of Acoustic and Temperature

Liu

Wang

et al. 2019

IEEE Photonics J.

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A compact fiber optic Fabry-Perot (F-P) sensor for simultaneous acoustic and temperature measurement has been proposed in the research. The sensor consists of silicon-glass-silicon sandwich structure by anodic bonding. The air F-P cavity with a circular hole and slots utilizes the deformation of the silicon membrane to realize acoustic measurement, and the silicon F-P cavity utilizes the temperature sensitivity of the refractive index of silicon to realize temperature measurement. The acoustic signal and temperature information could be recovered by acoustic and temperature demodulation method, respectively. The experimental results demonstrate that the sensor has a signal-to-noise ratio (SNR) of 53 dB and the acoustic sensitivity of 4.65 mV/Pa at 21 kHz, and the temperature sensitivity of 123.10 nm/°C at 20°C∼120°C. The proposed fiber optic F-P sensor has great potential for simultaneous acoustic and temperature measurement in aviation, due to its compact structure, mass production and immunity to electromagnetic interference.

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“…ω is the mass density of the membrane. For silicon material, E = 190 GPa, μ = 0.278, ω = 2.33 g/cm 3 . Figs.…”

Section: Acoustic Sensing Principlementioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

A Compact Fiber Optic Fabry–Perot Sensor for Simultaneous Measurement of Acoustic and Temperature

Liu

Wang

et al. 2019

IEEE Photonics J.

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“…The calculation of p t from the five pressure ports per probe is described in (Johansen et al, 2001). Total pressure distortion in the AIP is an indicator for stable engine operation (Braithwaite and Soedert, 1980). To assess the nonuniformity of the total pressure distribution in the AIP, the total pressure distortion is evaluated referring to Welte (1986).…”

Section: Test Parametermentioning

confidence: 99%

Aerodynamic characteristics of helicopter engine side air intakes

Knoth

Breitsamter

2018

AEAT

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PurposeAerodynamic characteristics of engine side air intakes for a lightweight helicopter are investigated aiming to achieve an efficient engine airframe integration. Design/methodology/approachOn a novel full-scale model of a helicopter fuselage section, a comprehensive experimental data set is obtained by wind tunnel testing. Different plenum chamber types along with static side intake and semi-dynamic side intake configurations are considered. Engine mass flow rates corresponding to the power requirements of realistic helicopter operating conditions are reproduced. For a variety of freestream velocities and mass flow rates, five-hole pressure probe data in the aerodynamic interface plane and local surface pressure distributions are compared for the geometries. FindingsIn low-speed conditions, unshielded, sideways facing air intakes yield lowest distortion levels and total pressure losses. In fast forward flight condition, a forward-facing intake shape is most beneficial. Additionally, the influence of an intake grid and plenum chamber splitter is evaluated. Originality/valueThe intake testing approach and the trends found can be applied to other novel helicopter intakes in early development stages to improve engine airframe integration and decrease development times.

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“…The surrounding air flows into this region causing transverse velocities. 39 Twin swirl consists of two counter rotating components in the duct cross-section. Twin swirl is produced in all curved ducts as a result of the conservation of angular momentum.…”

Section: Swirl Distortionmentioning

confidence: 99%

Progress in Boundary Layer Ingesting Embedded Engine Research

Ferrar¹,

O’Brien²

2012

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

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Modern aviation requirements for energy efficiency and environmental compatibility push air vehicle development toward highly integrated systems in which each component, and the system, is optimized for overall performance. Embedded engines and boundary layer ingesting propulsion systems have the potential to simultaneously improve fuel burn, noise, and emissions. Energizing the boundary layer of a drag-producing object has been recognized as a viable method to effectively reduce drag as part of the propulsion process for many years. For decades, investigators have suggested different methods for energizing boundary layers with propulsion systems. A wealth of publications forms a body of work including mathematical predictions of the effects of boundary layer ingestion and explanations of the physical basis for the process. This paper seeks to present a review of this work, in light of results from current research, to provide a reference and vision for the continuing development of boundary layer ingesting embedded engine technology.

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Combined Pressure and Temperature Distortion Effects on Internal Flow of a Turbofan Engine

Cited by 12 publications

References 2 publications

A Compact Fiber Optic Fabry–Perot Sensor for Simultaneous Measurement of Acoustic and Temperature

A Compact Fiber Optic Fabry–Perot Sensor for Simultaneous Measurement of Acoustic and Temperature

Aerodynamic characteristics of helicopter engine side air intakes

Progress in Boundary Layer Ingesting Embedded Engine Research

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