Aircraft Engine Design, Third Edition

Mattingly, Jack D.; Heiser, William H.; Pratt, David T.; Boyer, Keith M.; Haven, Brenda

doi:10.2514/4.105173

Cited by 39 publications

(47 citation statements)

References 1 publication

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“…The isentropic velocity (V s ) and the ideal mass flow rate and are calculated using equations (7) and 8, respectively. 4,22 Where NPR…”

Section: Nozzle Performance Calculation Methodsmentioning

confidence: 99%

“…3 The discharge coefficient (C d ) is the measure of the reduction in nozzle mass flow relative to the ideal condition and is related to the required physical nozzle exit area to match the gas turbine thermodynamic cycle. 4 In addition to the operating conditions, the nozzle performance is affected by a number of geometrical aspects. 3,5 Thornock et al 5 reported that the C d is a function of the primary nozzle angle of the internal walls.…”

Section: Introductionmentioning

confidence: 99%

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Computational fluid dynamics-based approach for low-order models of propelling nozzle performance

Al-Akam

Nikolaidis

MacManus

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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At the preliminary design stage for an aero-engine, the evaluation of the nozzle performance is an important aspect as it affects the overall engine cycle behaviour. Currently, there is a lack of systematic, extensive data on the nozzle performance and its dependence on the geometric and aerodynamic aspects. This paper presents a method that can be used to build characteristic maps for a nozzle as a function of a number of geometric and aerodynamic parameters. The proposed method encompasses the design of a nozzle configuration, a parameterisation of the nozzle pressure ratio, nozzle contraction ratio, plug half-angle (β), mesh generation, and an aerodynamic assessment using the Favre-averaged Navier–Stokes method. The method has been validated against experimental performance data of a plug nozzle configuration and then used for the aerodynamic assessment. The derived nozzle maps show that the thrust coefficient ( Cfg) for this type of nozzle is significantly sensitive to the combined effect of the variation of the proposed parameters on the nozzle performance. These maps were used to build low-order models to predict Cfg, using response surface methods. The performance was assessed, and the results show that these low-order methods are capable of providing Cfg estimates with sufficient accuracy for use in preliminary design assessments.

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“…The isentropic velocity (V s ) and the ideal mass flow rate and are calculated using equations (7) and 8, respectively. 4,22 Where NPR…”

Section: Nozzle Performance Calculation Methodsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Computational fluid dynamics-based approach for low-order models of propelling nozzle performance

Al-Akam

Nikolaidis

MacManus

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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“…The inlets of exhaust systems (boundary A and B) are set to as the pressure-inlet boundary condition, and the gas state parameters can be calculated from the overall performance of the engine. 26 The total pressure and total temperature of boundary A are 0.105 MPa and 850 K, respectively, and the total pressure and total temperature of boundary B are 0.104 MPa and 367 K, respectively. Meanwhile, the mass fraction of the mixed gas originating from the combustor, which is composed of N 2 , O 2 , CO 2 , and H 2 O, can also be obtained from the engine performance calculation.…”

Section: Computational Domain and Boundary Conditionsmentioning

confidence: 99%

The influence of nozzle deflection on fluid dynamic and infrared characteristics of a two-dimensional convergent–divergent vectoring exhaust system

Wang

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Superior maneuverability and good infrared stealthy properties are two key points of the future aircraft. A two-dimensional convergent–divergent (2D-CD) vectoring exhaust system can improve the maneuverability of aircrafts and has been widely applied to the latest generation aircrafts. Understanding fluid dynamic and infrared radiation characteristics of the 2D-CD vectoring exhaust systems under different conditions of the nozzle deflection is very crucial, which can provide significant information for the suppression of the infrared radiation property of the 2D-CD vectoring exhaust system. In this paper, by means of computational fluid dynamics, the fluid dynamic and infrared radiation characteristics of the 2D-CD vectoring exhaust system are studied at subsonic cruise status with nozzle deflection angles from 0 to 20°, and the results are compared with those of the baseline axisymmetric exhaust system. The results indicate that the fluid dynamic performance of a properly designed 2D-CD vectoring exhaust system is equivalent to the fluid dynamic performance of the baseline axisymmetric exhaust system. When the nozzle deflection angle is less than 5°, the mass flow and thrust force of the 2D-CD vectoring exhaust system are almost unchanged, and with the increase of the nozzle deflection angles, the mass flow and thrust force decrease rapidly. The thrust force deflection angles lag behind the nozzle deflection angles all the time, and as the nozzle deflection angle increases, the difference between them decreases. The direction of the maximum infrared radiation of the 2D-CD vectoring exhaust system deflects with the deflection of the nozzle, and the mean integrated infrared radiation intensity of the exhaust system decreases with the increase of nozzle deflection angles.

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“…Conditions leading to the buzz according to Dailey criterion. 23 if its amplitude is large. 65 Thus, it must be prevented or delayed by the flow control methods such as the boundary layer suction.…”

Section: Effects Of the Bleed On Buzz Phenomenonmentioning

confidence: 99%

Boundary layer suction for high-speed air intakes: A review

Sepahi-Younsi

Feshalami

Maadi

et al. 2018

Proceedings of the Institution of Mechanical Engineers, Part G:

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The paper summarizes recent developments in boundary layer suction for high-speed air intakes. Bleed has been efficiently used in supersonic and hypersonic intakes for three primary reasons: to improve the performance of the intake, to reduce the starting Mach number of the intake, and to postpone the onset of buzz oscillations. A bleed system has many characteristics such as the bleed entrance and exit areas, bleed entrance slant angle and position, and bleed type (slot or porous and ram-scoop or flush). Each of these parameters has significant impacts on the intake performance and stability that have been reviewed in this study. In addition, the effectiveness of other flow control methods has been compared with the bleed method.

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Aircraft Engine Design, Third Edition

Cited by 39 publications

References 1 publication

Computational fluid dynamics-based approach for low-order models of propelling nozzle performance

Computational fluid dynamics-based approach for low-order models of propelling nozzle performance

The influence of nozzle deflection on fluid dynamic and infrared characteristics of a two-dimensional convergent–divergent vectoring exhaust system

Boundary layer suction for high-speed air intakes: A review

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