Rotor cavity flow and heat transfer with inlet swirl and radial inflow of cooling air
- GE Corporate Research and Development, Schenectady, NY (United States)
To improve the reliability of turbine disc life prediction, experimental verification is required of analytical tools that calculate the flow field and heat transfer coefficients in turbine-stator cavities. In these experiments a full-scale model of the aft (downstream) cavity of a typical aircraft gas turbine was employed using a high-molecular-weight gas (Refrigerant-12) at ambient pressure and temperature conditions to match the dimensionless parameters at engine conditions. The cavity temperature and selected cavity velocity profiles were measured. Electrical heat addition was employed with liquid crystal surface temperature measurement to obtain local disc heat transfer coefficients. Cooling gas flow was added with inlet swirl near the outer diameter of the rotor and discharged near the rotor hub. Rotational Reynolds numbers were varied up to 8 {times} 10{sup 6} with the swirl Reynolds number variation up to 1.4 {times} 10{sup 5}. Rotor heat transfer coefficients are larger when they are dominated by either the inlet swirl flow or by the rotor angular velocity and are the lowest when neither inlet swirl flow nor the rotor velocity are dominant. A CFD code was employed to illustrate the effect of the velocity field on disc heat transfer.
- OSTI ID:
- 449513
- Report Number(s):
- CONF-950828-; ISBN 0-7918-1706-7; TRN: IM9714%%70
- Resource Relation:
- Conference: 1995 National heat transfer conference, Portland, OR (United States), 5-9 Aug 1995; Other Information: PBD: 1995; Related Information: Is Part Of 1995 national heat transfer conference: Proceedings. Volume 5: Heat transfer in aerospace devices or systems; Heat pipes and thermosyphons; Gas turbine heat transfer; HTD-Volume 307; Downing, S.; Haas, L.; Chang, W.S.; McEligot, D.M. [eds.]; PB: 152 p.
- Country of Publication:
- United States
- Language:
- English
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