A CFD Analysis of the Flow in the Impeller Rear Cavity of Aeroengines

Liu, X.; Patel, Kanishk

doi:10.1115/93-gt-259

Cited by 4 publications

(3 citation statements)

References 11 publications

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“…For the swirl nozzle flow (Liu et al, 1995), excellent agreement between the calculation and the measurement was obtained. For the impeller rear cavity flow calculation (Liu et al,1993), fair agreement with measurement was found. However.…”

Section: The Calculation Methodsmentioning

confidence: 71%

Flow in a Corotation Radial Inflow Cavity Between Turbine Disk and Coverplate

Liu¹

1997

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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In order to guide the design of the engine air system, a comprehensive CFD analysis has been carried out on the flow in a corotation radial inflow cavity between the turbine disk and the coverplate of a gas turbine engine. Nine different flow cases have been studied. The rotational Reynolds number ranges from 0.79×106 to 3.14×106, and the through flow number ranges from 7×103 to 194×103, which covers the whole envelope of engine operating conditions. The CFD results revealed the complicated source-sink flow physics, and provided detailed variation of pressure, temperature, swirl factor and moment coefficient, etc., which serve as the basis for engine air system modelling. It has been shown that the flow behaves more and more like a free vortex with increasing mass flow, but more and more like a forced vortex with increasing rotational speed. For a good engine air system design, it is preferred to introduce the air into the cavity in such a way that the inlet swirl factor is independent of the mass flow.

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Section: The Calculation Methodsmentioning

confidence: 71%

Flow in a Corotation Radial Inflow Cavity Between Turbine Disk and Coverplate

Liu¹

1997

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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“…Hence an understanding of the variation in static pressure distribution as bleed air is passed through the impeller rear face cavity is of extreme importance to the design of the internal air system of the engine. This may be achieved for each particular design case by the use of component test rigs or detailed CFD analysis such as that performed by Liu and Patel (1993). However, there is a need in industry for simpler but adequate analysis methods that can be used frequently in the parametric studies associated with the preliminary design process.…”

Section: Figure 1 Typical Impeller Rear Face Rotor-stator Cavity Confmentioning

confidence: 99%

Simple Design Methods for the Prediction of Radial Static Pressure Distributions in a Rotor-Stator Cavity With Radial Inflow

Hart

Turner

1995

Volume 1: Turbomachinery

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Research has been conducted into the effects of component geometry and air bleed flow on the radial variation of static pressure and core tangential velocity in a rotor-stator cavity of the type often found behind the impeller of a gas turbine engine centrifugal compressor. A CFD code, validated by rig test data for a wide range of rotor-stator axial gaps and throughflows, has been used to generate pressure and velocity data for typical gas turbine operating conditions. This data has been arranged as a series of simple design curves which relate the rotational speed of the core of fluid between rotor and stator boundary layers, and hence the static pressure distribution, to primary cavity geometry, rotational Reynolds number and bleed throughflow with particular attention to radial inflowing bleeds. Details are provided on the use and limitations of these curves. Predictions using this method have been compared successfully with measured data from engine test and a compressor test rig, modified to facilitate variable quantity and direction of impeller rear face bleed flow, at typical gas turbine operational power conditions. Data generated by these curves can be used directly in the design process and to validate integral momentum methods which can provide relatively simple computation of rotor-stator cavity pressure and velocity distributions independently or within air system network programs. This approach is considered to be a cost and time effective addition to the analytical design process especially if validated CFD code, which can accommodate rotational flows consistently and accurately, is not available.

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“…A considerable amount of work about the flow characteristics in the rotor-stator cavity with a centripetal inflow has been carried out by a number of workers [1][2][3][4][5][6]. The results show that for a rotor-stator cavity with centripetal flow, the internal flow conforms to the Batchelor type which consisted of an inviscid core and two Ekman type boundary layers.…”

Section: Introductionmentioning

confidence: 99%

Computational Investigation of Flow Control Methods in the Impeller Rear Cavity

Liu

et al. 2020

International Journal of Aerospace Engineering

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In typical median and small aeroengines, the air used to realize the functions such as cooling of turbine blades and disks, sealing of turbine cavities and bearing chambers, adjusting of rotating assembly axial load is normally drawn through the rear cavity of centrifugal impeller, so the thorough understanding of flow characteristics and pressure distribution and the proposal of the corresponding control methods in the cavity are the key to design the rational secondary air system. With an impeller rear cavity in a small turbofan engine as an object, the current study was dedicated to the investigation of flow control methods in the cavity. Two methods, namely, baffle and swirl-controlled orifice, were proposed to regulate the pressure loss and distribution in the cavity. Furthermore, the influence of geometry parameters of the two methods such as the length of baffle, the space between the baffle and rotating disk wall, the orientation, and radial position of swirl-controlled orifice was investigated. The CFD results show that the swirl-controlled orifice which could deswirl the flow is more effective in regulating the pressure loss and its distribution in cavity than baffle. The variation of the radial position of the swirl-controlled orifice had little influence on pressure loss but obvious influence on pressure distribution; therefore, decreasing the radial position could reduce the axial load on the rotating disk without changing the outlet pressure.

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A CFD Analysis of the Flow in the Impeller Rear Cavity of Aeroengines

Cited by 4 publications

References 11 publications

Flow in a Corotation Radial Inflow Cavity Between Turbine Disk and Coverplate

Flow in a Corotation Radial Inflow Cavity Between Turbine Disk and Coverplate

Simple Design Methods for the Prediction of Radial Static Pressure Distributions in a Rotor-Stator Cavity With Radial Inflow

Computational Investigation of Flow Control Methods in the Impeller Rear Cavity

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