LOW SUBSONIC SPEED NASA GENERATOR
LOW SUBSONIC SPEED NASA CODE
LOW SUBSONIC SPEED NASA WINDOWS

The shaft has a 1” bore, which provides the capability to pass wiring from rotating turbine-measurement instruments to a 100-channel slip ring.

LOW SUBSONIC SPEED NASA GENERATOR

Once at speed, the synch machine transitions from motor to generator as turbine airflow is introduced and the resultant turbine shaft power must be absorbed. The turbine is motored to desired speed by a 12,420-hp synchronous machine and gearbox (7.871:1 ratio).

LOW SUBSONIC SPEED NASA CODE

Data from detailed flow-field measurements, unsteady effects, and interaction effects provide better understanding of flow physics through a multistage turbine and provide a database to use in CFD code validation. Electrically-heated secondary air provides simulated coolant bleeds at desired temperature ratios, including provisions for heated air to control shroud growth and rotor clearances. W-6A is supplied with 40-psig air, which is then heated by natural-gas fired combustors, drives the research turbine and exits through a torus-like collector into the altitude exhaust system. As a turbine testing facility, these improvements are intended to better facilitate research in advanced turbine design features and improve the fundamental understanding of the dominant flow phenomena in multistage high pressure (HP) and low pressure (LP) axial turbines. The W-6A facility has undergone several recent enhancements that have resulted in upgraded capabilities that include enhanced power absorption, upgraded torque measurement, and improved flow measurement, to name a few. Data recording, processing, and display are accomplished through the facility’s distributed data acquisition system, with input data from analog and discrete inputs or steady-state pressure inputs from the Electronic Scanned Pressure (ESP) system. Data such as pressures, temperatures, and flow angles are measured in both rotating and nonrotating passages using standard instrumentation, hot wires, flow visualization, trace gases, and LDV, PIV and pressure sensitive paint.

LOW SUBSONIC SPEED NASA WINDOWS

Optical access windows in the compressor casing are used in conjunction with nonintrusive measurements and flow visualization techniques. The detailed flowfield measurements will assess the emerging CFD codes as well as provide data for the development of flow models required by the CFD codes. The increased size and low speed permits instrumentation to be located directly in the compressor’s complex flow paths. The compressor rotor is driven by a 1500-hp variable speed drive motor. Airflow exiting the compressor is controlled by a throttle valve, close coupled to the collector, and discharged into the atmospheric (axial) or altitude (centrifugal) exhaust system. The axial compressor has been configured for injection of air through the stator footring, stator blades and endwalls to assess flow control. The axial compressor has a removable casing treatment under rotor one and rotor three, which allows for various tip treatment studies. Air enters the facility through a filtered roof vent, is conditioned for temperature and turbulence, and then passes through the research compressor. Designed for a 4-ft diameter axial flow compressor, W-1A can be also be restored to facilitate a 5-ft diameter centrifugal flow compressor. This unique facility provides for an increased understanding of the complex flow phenomena within the curved centrifugal channels and multi-stage axial compressors. Two 14-channel magnetic tape recorders are used for dynamic data and the LDV system measures flow path behavior.

This facility is used to test compressors for gas turbine engines at conditions similar to those found in normal use as well as advanced concepts.Ī distributed data acquisition system provides on-line and post-run processing ESCORT-D handles up to 576 channels of analog inputs both steady state and discrete from an ESP system. The rig can accommodate compressors up to 20 in. Air enters the inlet plenum tank, passes through the compressor, and discharges through a throttle valve and cooling water spray before it enters the altitude or atmospheric exhaust system. The compressor can draw air from either an atmospheric intake, a 40-psig pressure source, or 10-psig refrigerated air system. The facility consists of a 6000-hp motor/gearbox which drives a research compressor at speeds up to 60,000 rpm achieving overall pressure ratios up to 30:1. This facility provides the capability for investigating the performance of advanced single- and multistage axial and centrifugal compressors, and various stage combinations over a wide range of speed, power, and mass flow. Home > Facilities > Engine Research Building Turbomachinery Facilities Small Engine Components Compressor Test Facility (CE-18)

Low subsonic speed nasa