Flow and heat transfer in a pre-swirl rotor-stator system

M Wilson, R G Pilbrow, J M Owen

Research output: Contribution to conferencePaper

Abstract

Conditions in the internal-air system of a high- pressure turbine stage are modelled using a rig comprising an outer pre-swirl chamber separated by a seal from an inner rotor-stator system. Pre-swirl nozzles in the stator supply the "blade cooling" air, which leaves the system via holes in the rotor, and disc-cooling air enters at the centre of the system and leaves through clearances in the peripheral seals. The experimental rig is instrumented with thermocouples, fluxmeters, pitot tubes and pressure taps enabling temperatures, heat fluxes, velocities and pressures to be measured at a number of radial locations. For rotational Reynolds numbers, the swirl ratio and the ratios of disc-cooling and blade-cooling flow rates are chosen to be representative of those found inside gas turbines. Measured radial distributions of velocity, temperature and Nusselt number are compared with computations obtained from an axisymmetric elliptic solver, featuring a low-Reynolds-number K-e turbulence model. For the inner rotor-stator system, the computed core temperatures and velocities are in good agreement with measured values, but the Nussel numbers are underpredicted. For the outer pre-swirl chamber, it was possible to make comparisons between the measured and computed values for cooling-air temperatures but not for the Nusselt numbers. As expected, the temperature of the blade-cooling air decreases as the swirl ratio increase, but the computed air temperatures are significantly lower than the measured ones. Overall, the results give valuable insight into some of the heat transfer characteristics of this complex system
Original languageEnglish
Publication statusPublished - Jun 1995
EventASME International Gas Turbine and Aero Engine Congress - Houston, Texas
Duration: 1 Jun 1995 → …

Conference

ConferenceASME International Gas Turbine and Aero Engine Congress
CityHouston, Texas
Period1/06/95 → …

Fingerprint

Stators
Rotors
Heat transfer
Cooling
Air
Nusselt number
Temperature
Seals
Fluxmeters
Reynolds number
Rotors (windings)
Thermocouples
Turbulence models
Gas turbines
Heat flux
Large scale systems
Nozzles
Turbines
Flow rate

Cite this

Wilson, M., Pilbrow, R. G., & Owen, J. M. (1995). Flow and heat transfer in a pre-swirl rotor-stator system. Paper presented at ASME International Gas Turbine and Aero Engine Congress, Houston, Texas, .

Flow and heat transfer in a pre-swirl rotor-stator system. / Wilson, M; Pilbrow, R G; Owen, J M.

1995. Paper presented at ASME International Gas Turbine and Aero Engine Congress, Houston, Texas, .

Research output: Contribution to conferencePaper

Wilson, M, Pilbrow, RG & Owen, JM 1995, 'Flow and heat transfer in a pre-swirl rotor-stator system' Paper presented at ASME International Gas Turbine and Aero Engine Congress, Houston, Texas, 1/06/95, .
Wilson M, Pilbrow RG, Owen JM. Flow and heat transfer in a pre-swirl rotor-stator system. 1995. Paper presented at ASME International Gas Turbine and Aero Engine Congress, Houston, Texas, .
Wilson, M ; Pilbrow, R G ; Owen, J M. / Flow and heat transfer in a pre-swirl rotor-stator system. Paper presented at ASME International Gas Turbine and Aero Engine Congress, Houston, Texas, .
@conference{e4645ec8f493451094555757680ecd68,
title = "Flow and heat transfer in a pre-swirl rotor-stator system",
abstract = "Conditions in the internal-air system of a high- pressure turbine stage are modelled using a rig comprising an outer pre-swirl chamber separated by a seal from an inner rotor-stator system. Pre-swirl nozzles in the stator supply the {"}blade cooling{"} air, which leaves the system via holes in the rotor, and disc-cooling air enters at the centre of the system and leaves through clearances in the peripheral seals. The experimental rig is instrumented with thermocouples, fluxmeters, pitot tubes and pressure taps enabling temperatures, heat fluxes, velocities and pressures to be measured at a number of radial locations. For rotational Reynolds numbers, the swirl ratio and the ratios of disc-cooling and blade-cooling flow rates are chosen to be representative of those found inside gas turbines. Measured radial distributions of velocity, temperature and Nusselt number are compared with computations obtained from an axisymmetric elliptic solver, featuring a low-Reynolds-number K-e turbulence model. For the inner rotor-stator system, the computed core temperatures and velocities are in good agreement with measured values, but the Nussel numbers are underpredicted. For the outer pre-swirl chamber, it was possible to make comparisons between the measured and computed values for cooling-air temperatures but not for the Nusselt numbers. As expected, the temperature of the blade-cooling air decreases as the swirl ratio increase, but the computed air temperatures are significantly lower than the measured ones. Overall, the results give valuable insight into some of the heat transfer characteristics of this complex system",
author = "M Wilson and Pilbrow, {R G} and Owen, {J M}",
year = "1995",
month = "6",
language = "English",
note = "ASME International Gas Turbine and Aero Engine Congress ; Conference date: 01-06-1995",

}

TY - CONF

T1 - Flow and heat transfer in a pre-swirl rotor-stator system

AU - Wilson, M

AU - Pilbrow, R G

AU - Owen, J M

PY - 1995/6

Y1 - 1995/6

N2 - Conditions in the internal-air system of a high- pressure turbine stage are modelled using a rig comprising an outer pre-swirl chamber separated by a seal from an inner rotor-stator system. Pre-swirl nozzles in the stator supply the "blade cooling" air, which leaves the system via holes in the rotor, and disc-cooling air enters at the centre of the system and leaves through clearances in the peripheral seals. The experimental rig is instrumented with thermocouples, fluxmeters, pitot tubes and pressure taps enabling temperatures, heat fluxes, velocities and pressures to be measured at a number of radial locations. For rotational Reynolds numbers, the swirl ratio and the ratios of disc-cooling and blade-cooling flow rates are chosen to be representative of those found inside gas turbines. Measured radial distributions of velocity, temperature and Nusselt number are compared with computations obtained from an axisymmetric elliptic solver, featuring a low-Reynolds-number K-e turbulence model. For the inner rotor-stator system, the computed core temperatures and velocities are in good agreement with measured values, but the Nussel numbers are underpredicted. For the outer pre-swirl chamber, it was possible to make comparisons between the measured and computed values for cooling-air temperatures but not for the Nusselt numbers. As expected, the temperature of the blade-cooling air decreases as the swirl ratio increase, but the computed air temperatures are significantly lower than the measured ones. Overall, the results give valuable insight into some of the heat transfer characteristics of this complex system

AB - Conditions in the internal-air system of a high- pressure turbine stage are modelled using a rig comprising an outer pre-swirl chamber separated by a seal from an inner rotor-stator system. Pre-swirl nozzles in the stator supply the "blade cooling" air, which leaves the system via holes in the rotor, and disc-cooling air enters at the centre of the system and leaves through clearances in the peripheral seals. The experimental rig is instrumented with thermocouples, fluxmeters, pitot tubes and pressure taps enabling temperatures, heat fluxes, velocities and pressures to be measured at a number of radial locations. For rotational Reynolds numbers, the swirl ratio and the ratios of disc-cooling and blade-cooling flow rates are chosen to be representative of those found inside gas turbines. Measured radial distributions of velocity, temperature and Nusselt number are compared with computations obtained from an axisymmetric elliptic solver, featuring a low-Reynolds-number K-e turbulence model. For the inner rotor-stator system, the computed core temperatures and velocities are in good agreement with measured values, but the Nussel numbers are underpredicted. For the outer pre-swirl chamber, it was possible to make comparisons between the measured and computed values for cooling-air temperatures but not for the Nusselt numbers. As expected, the temperature of the blade-cooling air decreases as the swirl ratio increase, but the computed air temperatures are significantly lower than the measured ones. Overall, the results give valuable insight into some of the heat transfer characteristics of this complex system

M3 - Paper

ER -