The development of a large annular facility for testing gas turbine combustor diffuser systems

Wray, A. P.; Carrotte, J. F.; Wilson, C. W.

doi:10.2514/6.1993-2546

Cited by 21 publications

(12 citation statements)

References 2 publications

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“…9) to commission the facility, validate the compressor design and establish a time-average data set including component and system performance data. Suitably calibrated and employed in the non-nulled mode, in line with Wray et al 17 , the five-hole probes provide the time-averaged local flow vector and total and static pressures. The probes used were manufactured in-house from stainless steel tubing of diameter 0.5mm and had an overall diameter of approximately 1.75mm.…”

Section: Five-hole Probementioning

confidence: 98%

Experimental Study of the Unsteady Aerodynamics the Compressor-Combustor Interface of a Lean Burn Combustion System

Walker

Carrotte

Peacock

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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Section: Five-hole Probementioning

confidence: 98%

Experimental Study of the Unsteady Aerodynamics the Compressor-Combustor Interface of a Lean Burn Combustion System

Walker

Carrotte

Peacock

et al. 2013

49th AIAA/ASME/SAE/ASEE Joint Propulsion Conference

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“…Suitably calibrated and employed in the non-nulled mode, in line with Wray et al [18], these provide the time-averaged local flow vector and total and static pressures. The probes could be traversed radially and circumferentially such that area traverses were constructed over repeatable sectors at the velocity normal to the traverse plane, Ū, was obtained by area-weighting the individual values whilst the total, , and static, , pressures were mass-weighted using the technique described by Klein [19].…”

Section: Instrumentation Data Reduction and Errorsmentioning

confidence: 99%

Impact of a Cooled Cooling Air System on the External Aerodynamics of a Gas Turbine Combustion System

Walker

Koli

Guo

et al. 2017

Journal of Engineering for Gas Turbines and Power

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To manage the increasing turbine temperatures of future gas turbines a cooled cooling air system has been proposed. In such a system some of the compressor efflux is diverted for additional cooling in a heat exchanger (HX) located in the bypass duct. The cooled air must then be returned, across the main gas path, to the engine core for use in component cooling. One option is do this within the combustor module and two methods are examined in the current paper; via simple transfer pipes within the dump region or via radial struts in the prediffuser. This paper presents an experimental investigation to examine the aerodynamic impact these have on the combustion system external aerodynamics. This included the use of a fully annular, isothermal test facility incorporating a bespoke 1.5 stage axial compressor, engine representative outlet guide vanes (OGVs), prediffuser, and combustor geometry. Area traverses of a miniature five-hole probe were conducted at various locations within the combustion system providing information on both flow uniformity and total pressure loss. The results show that, compared to a datum configuration, the addition of transfer pipes had minimal aerodynamic impact in terms of flow structure, distribution, and total pressure loss. However, the inclusion of prediffuser struts had a notable impact increasing the prediffuser loss by a third and consequently the overall system loss by an unacceptable 40%. Inclusion of a hybrid prediffuser with the cooled cooling air (CCA) bleed located on the prediffuser outer wall enabled an increase of the prediffuser area ratio with the result that the system loss could be returned to that of the datum level.

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“…This provides a good compromise in terms of capturing the blade wakes, secondary and rotor tip leakage flows etc. that will have an important influence on the downstream diffusing ducts whilst avoiding the costs associated with using a multi-stage compressor to provide the inlet conditions [16].…”

Section: Experimental Test Facilitymentioning

confidence: 99%

Intercooled Aero-Gas-Turbine Duct Aerodynamics: Core Air Delivery Ducts

Walker¹,

Regunath²,

Carrotte³

et al. 2012

Journal of Propulsion and Power

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The development of a large annular facility for testing gas turbine combustor diffuser systems

Cited by 21 publications

References 2 publications

Experimental Study of the Unsteady Aerodynamics the Compressor-Combustor Interface of a Lean Burn Combustion System

Experimental Study of the Unsteady Aerodynamics the Compressor-Combustor Interface of a Lean Burn Combustion System

Impact of a Cooled Cooling Air System on the External Aerodynamics of a Gas Turbine Combustion System

Intercooled Aero-Gas-Turbine Duct Aerodynamics: Core Air Delivery Ducts

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