Windage Rise and Flowpath Gas Ingestion in Turbine Rim Cavities

Haaser, Fred G.; Jack, J B; McGreehan, William F.

doi:10.1115/1.3240090

Cited by 18 publications

(10 citation statements)

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“…In addition, the temperature of the fluid adjacent to the rotating disk will be raised up for viscous heating. The temperature rise of the coolant flowing through the disk cavity was measured by Hasser [17] using a real jet engine model. 3 Description of the Test Rig Figure 1 shows the general assembly of the test rig.…”

Section: Review Of Previous Workmentioning

confidence: 99%

Windage Heating in a Shrouded Rotor-Stator System

Tao

Zhang

Luo

et al. 2014

Journal of Engineering for Gas Turbines and Power

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This paper has experimentally and numerically studied the windage heating in a shrouded rotor-stator disk system with superimposed flow. Temperature rise in the radius direction on the rotating disk is linked to the viscous heating process when cooling air flows through the rotating component. A test rig has been developed to investigate the effect of flow parameters and the gap ratio on the windage heating, respectively. Experimental results were obtained from a 0.45 m diameter disk rotating at up to 12,000 rpm with gap ratio varying from 0.02 to 0.18 and a stator of the same diameter. Infrared temperature measurement technology has been proposed to measure the temperature rise on the rotor surface directly. The PIV technique was adapted to allow for tangential velocity measurements. The tangential velocity data along the radial direction in the cavity was compared with the results obtained by CFD simulation. The comparison between the free disk temperature rise data and an associated theoretical analysis for the windage heating indicates that the adiabatic disk temperature can be measured by infrared method accurately. For the small value of turbulence parameter, the gap ratio has limited influence on the temperature rise distribution along the radius. As turbulence parameter increases, the temperature rise difference is independent of the gap ratio, leaving that as a function of rotational Reynolds number and throughflow Reynolds number only. The PIV results show that the swirl ratio of the rotating core between the rotor and the stator has a key influence on the windage heating.

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Section: Review Of Previous Workmentioning

confidence: 99%

Windage Heating in a Shrouded Rotor-Stator System

Tao

Zhang

Luo

et al. 2014

Journal of Engineering for Gas Turbines and Power

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“…For both rotor and stator surfaces, the surface area moment is obtained by integrating over the intertooth cavity wall. Values of the surface friction coefficient are obtained by experiment or through the approximate expressions of Haaser et al (1987).…”

Section: Labyrinth Seal Windagementioning

confidence: 99%

“…The problem of high measured temperature rise in rotor cavities and seals of a gas turbine engine led to a series of studies on power dissipation. Work on cavity windage and gas path ingestion was presented by Haaser, Jack, and McGreehan (1987) using the approach of Daily and Nece (1960). The method employed a momentum balance to determine the tangential velocity of the core of rotating fluid within the cavity.…”

Section: Introductionmentioning

confidence: 99%

Power Dissipation in Smooth and Honeycomb Labyrinth Seals

McGreehan¹,

1989

Volume 1: Turbomachinery

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The surface frictional characteristics of a labyrinth seal can result in significant windage power dissipation for high speed seals. Recent advances in seal design have produced high speed, high pressure labyrinth seals which operate at very low leakage rates. The reduced leakage is beneficial to gas turbine efficiency, but seal discharge temperatures can approach material design limits with high windage power dissipation. Also, a high air temperature rise can influence seal leakage flow. Consequently, the general assumption of negligible rotational effect on leakage is not always valid. A method is presented for the prediction of seal power dissipation and leakage flow over a wide range of design parameters. Results are compared to available test data and several approaches examined for the reduction of seal windage.

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“…Compressibility of the flow was included in their analysis. Haaser, Jack and McGreehan (1987) provided a simple analytical approach for determining the bulk temperature rise in the cavity due to the hot gas ingestion from the mainstream as well as the frictional heating. Farthing and Owen (1987) obtained flow visualization and heat transfer measurements in an idealized cavity comprising two disks with a shroud.…”

Section: Introductionmentioning

confidence: 99%

Thermal Details in a Rotor-Stator Cavity at Engine Conditions With a Mainstream

Rhode

1991

Volume 1: Turbomachinery

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This investigation involves a numerical study of enclosed rotor-stator cavities of gas turbine engines. The complete elliptic form of the 2-D, axisymmetric Navier-Stokes equations for compressible turbulent flow were solved. Included are the complete fluid and thermal effects of the hot mainstream gas interacting with the cooling cavity purge flow at actual engine flow conditions for generalized geometries. Additional flow conditions above and below that for engine nominal conditions are also considered. The relationships among the important flow parameters are investigated by examining the entire set of computations. The predictions reveal that a small recirculation zone in the stator shroud axial gap region is the primary mechanism for the considerable thermal transport from the mainstream to the turbine blade root/retainer region of the rotor.

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Windage Rise and Flowpath Gas Ingestion in Turbine Rim Cavities

Cited by 18 publications

References 0 publications

Windage Heating in a Shrouded Rotor-Stator System

Windage Heating in a Shrouded Rotor-Stator System

Power Dissipation in Smooth and Honeycomb Labyrinth Seals

Thermal Details in a Rotor-Stator Cavity at Engine Conditions With a Mainstream

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