Installation of a Turbine Stage in the Pyestock Isentropic Light Piston Facility

Hilditch, M. A.; Fowler, Andrew; Jones, T. V.; Chana, K. S.; Oldfield, M. L. G.; Ainsworth, R. W.; Hogg, Simon; Anderson, Susan; Smith, Graham C.

doi:10.1115/94-gt-277

Cited by 38 publications

(23 citation statements)

References 17 publications

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“…The OTRF has been used to test a high pres sure (HP) turbine stage [31] and a 1.5 turbine stage turbine [32], A novel feature of the facility is the aerodynamic turbobrake [33], which is on the same shaft as the turbine and is driven by the tur bine exit-flow. At the design speed, the turbobrake power is matched with the turbine, and thus constant speed is maintained during a run.…”

Section: Oxford Turbines Research Facilitymentioning

confidence: 99%

Design of a Nonreacting Combustor Simulator With Swirl and Temperature Distortion With Experimental Validation

Hall

Chana

Povey

2014

Journal of Engineering for Gas Turbines and Power

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Nonuniform combustor outlet flows have been demonstrated to have significant impact on the first and second stage turbine aerothermal performance. Rich-burn combustors, which generally have pronounced temperature profiles and weak swirl profiles, primarily affect the heat load in the vane but both the heat load and aerodynamics of the rotor. Lean burn combustors, in contrast, generally have a strong swirl profile which has an additional significant impact on the vane aerodynamics which should be accounted for in the design process. There has been a move towards lean burn combustor designs to reduce NOx emissions. There is also increasing interest in fully integrated design proc esses which consider the impact of the combustor flow on the design of the high pressure vane and rotor aerodynamics and cooling. There are a number of current large research projects in scaled (low temperature and pressure) turbine facilities which aim to provide validation data and physical understanding to support this design philosophy. There is a small body of literature devoted to rich burn combustor simulator design but no open lit erature on the topic of lean burn simulator design. The particular problem is that in non reacting, highly swirling and diffusing flows, vortex instability in the form of a precessing vortex core or vortex breakdown is unlikely to be well matched to the reacting case. In reacting combustors the flow is stabilized by heat release, but in low temperature simula tors other methods for stabilizing the flow must be employed. Unsteady Reynoldsaveraged Navier-Stokes and large eddy simulation have shown promise in modeling swirling flows with unstable features. These design issues form the subject of this paper.

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Section: Oxford Turbines Research Facilitymentioning

confidence: 99%

Design of a Nonreacting Combustor Simulator With Swirl and Temperature Distortion With Experimental Validation

Hall

Chana

Povey

2014

Journal of Engineering for Gas Turbines and Power

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“…(1) The Isentropic Light Piston Facility (QinetiQ, Hamphsire, UK, 2002) [8], generates hot spots by the compression of air by a piston. This blow-down facility was recently upgraded (2008) [6] in order to get a strong, well-defined temperature profile, with low run-to-run variation, and using a rotatable device to study hot-streak-vanes clocking effect.…”

Section: Hot Streak Simulators In Turbine Testing Facilitiesmentioning

confidence: 99%

“…1 at vane inlet for all the main research facilities on hot streaks since the 1980s [5,6,[8][9][10][11][12][13]. 1 at vane inlet for all the main research facilities on hot streaks since the 1980s [5,6,[8][9][10][11][12][13].…”

Section: Hot Streak Simulators In Turbine Testing Facilitiesmentioning

confidence: 99%

Development of an Engine Representative Combustor Simulator Dedicated to Hot Streak Generation

Koupper¹,

Caciolli

Gicquel

et al. 2014

Journal of Turbomachinery

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Development of an Engine Representative Combustor Simulator Dedicated to Hot Streak GenerationNowadays, the lack of confidence in the prediction of combustor-turbine interactions and more specifically our ability to predict the migration of hot spots through this interface leads to the application of extra safety margins, which are detrimental to an optimized turbine design and efficiency. To understand the physics and flow at this interface, a full 360 deg nonreactive combustor simulator (CS) representative of a recent lean burn chamber together with a 1.5 turbine stage is instrumented at DLR in Gottingen (Germany) within the European project FACTOR. The chamber operates with axial swirlers especially designed to reproduce engine-realistic velocity and temperature distortion profiles, allowing the investigation of the hot streaks transport through the high pressure (HP) stage. First, a true scale three injector annular sector of the CS without turbine is assembled and tested at the University of Florence. To generate the hot steaks, the swirlers are fed by an air flow at 531 K, while the liners are cooled by an effusion system fed with air at ambient temperature. In addition to static pressure taps and thermocouples, the test rig will be equipped with an automatic traverse system which allows detailed measurements at the combustor exit by means of a 5-hole probe, a thermocouple, and hot wire anemometers. This paper presents the design process and instrumentation of the trisector CS, with a special focus on large Eddy simulations (LES) which were widely used to validate the design choices. It was indeed decided to take advantage of the ability and maturity of LES to properly capture turbulence and mixing within combustion chambers, despite an increased computational cost as compared to usual Reynolds averaged Navier Stokes (RANS) approaches. For preliminary design, simulations of a single periodic sector (representative of the DLR full annular rig) are compared to simulations of the trisector test rig, showing no difference on the central swirler predictions, comforting the choice for the trisector. In parallel, to allow hot wire anemometry (HWA) measurements, the selection of an isothermal operating point, representative of the nominal point, is assessed and validated by use of LES.

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“…The ILPF has been used to test a highpressure (HP) turbine stage [4], and a 1.5 turbine stage turbine [5]. For the experiments described in this paper, only the HP stage was installed.…”

Section: Description Of the Facilitymentioning

confidence: 99%

A hot-streak (combustor) simulator suited to aerodynamic performance measurements

Povey

Qureshi

2008

Proceedings of the Institution of Mechanical Engineers, Part G:

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A new hot-streak (combustor) simulator has been designed and implemented in a turbine test facility at QinetiQ Farnborough (the QinetiQ Isentropic Light Piston Facility, ILPF) to study the impact of temperature distortion on high pressure (HP) turbine efficiency, aerodynamics, and heat transfer. The ILPF is an engine scale, short duration, rotating transonic turbine test facility, in which M , Re, T g /T w , and N / √ T are matched to engine conditions. The research forms part of the EU Turbine Aero-Thermal External Flows (TATEF II) programme.The hot-streak simulator is a second-generation design, in which cold gas is introduced into a hot mainstream though radial and circumferential slots upstream of the turbine stage. The simulator is rotatable, so the effect of clocking (relative circumferential position of hot streak and nozzle guide vane leading edge) can easily be investigated. An emphasis was placed on accurate measurement of turbine inlet enthalpy flux so that the impact of hot streaks on turbine efficiency could be investigated.The hot-streak simulator differs from all previous systems in that a pronounced radial and circumferential temperature profile has been generated, with a hot-streak to vane count of 1:1. The profile is very well matched (non-dimensionally) to the target profile, which is a combustor temperature profile measured in a modern operating engine at the most extreme point in the cycle. The most accurate area survey of a simulated temperature profile has been conducted to date, and this demonstrates that the simulator offers an exceptionally high degree of circumferential symmetry and run-to-run repeatability.The design and commissioning of the simulator is described, and the measured temperature profiles are compared with the target profile.

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Installation of a Turbine Stage in the Pyestock Isentropic Light Piston Facility

Cited by 38 publications

References 17 publications

Design of a Nonreacting Combustor Simulator With Swirl and Temperature Distortion With Experimental Validation

Design of a Nonreacting Combustor Simulator With Swirl and Temperature Distortion With Experimental Validation

Development of an Engine Representative Combustor Simulator Dedicated to Hot Streak Generation

A hot-streak (combustor) simulator suited to aerodynamic performance measurements

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