The LEMCOTEC 1½ Stage Film-Cooled HP Turbine: Design, Integration and Testing in the Oxford Turbine Research Facility

Beard, Paul F.; Adams, Maxwell G.; Nagawakar, Jethru R; Stokes, Mark; Wallin, Fredrik; Cardwell, David; Povey, Thomas; Chana, K. S.

doi:10.29008/etc2019-216

Cited by 6 publications

(9 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The predicted changes (with swirl) in cooled vane loading distributions are consistent with the measurements on the uncooled vanes at 10% span, except for (x/C ax > 0.7), where the measured static pressures are up to 10% lower than the predictions. This likely results from a difference in vane throat area between the experimental and CFD geometries (smaller throat area in experiment), as discussed by Beard et al [31]. There is also a reduction in measured static pressure on both vanes (by up to 10%) with nonuniform inlet conditions at the x/C ax = 0.72 tapping.…”

Section: High-pressure Vane Aerodynamicsmentioning

confidence: 83%

“…For the present investigation, the facility was fitted with the LEMCOTEC 1.5-stage research turbine. The design and commissioning of the LEMCOTEC turbine was reported by Beard et al [31]. Figure 1 presents vane/blade mid-span sections and a meridional schematic of the annulus line.…”

Section: Methodsmentioning

confidence: 99%

“…First, the swirl profile was much more aggressive (peak swirl angles were greater than ±40 deg compared with approximately ±30 deg in the present study). Second, the vane had been designed for uniform inlet conditions, whereas the vane in the present study was designed for robustness to inlet swirl [31].…”

Section: High-pressure Vane Aerodynamicsmentioning

confidence: 99%

See 2 more Smart Citations

Effect of a Combined Hot-Streak and Swirl Profile on Cooled 1.5-Stage Turbine Aerodynamics: An Experimental and Computational Study

Adams

Beard

Stokes

et al. 2021

Journal of Turbomachinery

Self Cite

View full text Add to dashboard Cite

Recently developed lean-burn combustors offer reduced NOx emissions for gas turbines. The flow at exit of lean-burn combustors is dominated by hot-streaks and residual swirl, which have been shown–individually–to impact turbine aerodynamic performance. Studies have shown that residual swirl at inlet to the high-pressure (HP) stage predominantly affects the vane aerodynamics, while hot-streaks affect the rotor aerodynamics. Studies have also shown that these changes to the HP stage aerodynamics can affect the downstream intermediate-pressure (IP) vane aerodynamics. Yet, to date, there have been no published studies presenting experimental turbine test data with both swirl and hot-streaks simultaneously present at inlet. This paper presents the first experimental and computational investigation into the effects of combined hot-streaks and swirl on turbine aerodynamics. Measurements were conducted in the Oxford Turbine Research Facility, a short-duration rotating transonic facility that matches non-dimensional engine conditions. Two turbine inlet flows are considered. The first is uniform in total pressure, total temperature, and flow angle. The second features a non-uniform total temperature (hot-streak) profile featuring strong radial and weak circumferential variation superimposed on a swirling velocity profile. Area surveys of the flow were conducted throughout the turbine. Measurements and URANS predictions suggest that the inlet temperature non-uniformity was relatively well preserved upon being convected through the turbine, and relatively poor comparisons between URANS and experiment highlight the challenge of accurately predicting the complex IP vane flow.

show abstract

Section: High-pressure Vane Aerodynamicsmentioning

confidence: 83%

Section: Methodsmentioning

confidence: 99%

See 1 more Smart Citation

Effect of a Combined Hot-Streak and Swirl Profile on Cooled 1.5-Stage Turbine Aerodynamics: An Experimental and Computational Study

Adams

Beard

Stokes

et al. 2021

Journal of Turbomachinery

Self Cite

View full text Add to dashboard Cite

show abstract

“…These measurements, presented in Ref. [11], showed no significant circumferential variation in the casing static pressure, suggesting that the error introduced by neglecting circumferential variation in the row exit static pressures would be relatively small. With regard to the second effect, shown by Collins and Povey [4], who first reported this phenomenon, these acoustic effects can result in time-averaged coolant mass flowrates that differ from those calculated using a steady capacity characteristic with time-instantaneous pressure ratios across the holes (the so-called quasi-steady mass flowrate).…”

Section: Coolant Supply and Mass Flowmentioning

confidence: 88%

“…For the present investigation, the facility operated with the lowemissions core engine technologies (LEMCOTEC) turbine, a 1.5-stage research turbine designed by Rolls-Royce and GKN to represent modern engine architectures. The design and commissioning of the turbine is reported by Beard et al [11]. The design operating conditions of the LEMCOTEC turbine in the OTRF are presented in Table 2.…”

Section: Methodsmentioning

confidence: 99%

Impact of Rotor-Casing Effusion Cooling on Turbine Performance and Operating Point: An Experimental, Computational, and Theoretical Study

Adams

Adami

Collins

et al. 2021

Journal of Turbomachinery

Self Cite

View full text Add to dashboard Cite

It is known that a secondary effect of rotor-casing effusion cooling is to modify and potentially spoil the rotor over-tip leakage flow. Studies have shown both positive and negative impacts on high-pressure stage aerodynamic performance and heat transfer, although there remains no consensus on whether the net effect is beneficial when both aerodynamic and thermal effects are accounted for simultaneously. An effect that has not been extensively discussed in the literature is the change in stage operating point that arises due to mass introduction midway through the machine. This effect complicates the analysis of the true performance impact on a turbine and must be accounted for in an assessment of the overall benefit of such a system. In this paper, we develop a low-order (mean-line) analysis in an attempt to bring clarity to this issue. We then present results from experiments conducted in the Oxford Turbine Research Facility, a 1.5-stage transonic rotating facility capable of matching non-dimensional engine conditions, with effusion cooling implemented over a sector of the rotor casing. Finally, we present steady and unsteady Reynolds-Averaged Navier-Stokes (RANS) simulations both with and without cooling. The results are used show that with cooling, there are flow changes both locally to the cooled casing (changes to the tip-leakage and secondary flow structures) and globally (changes to the bulk-flow velocity triangles). For the present configuration, both changes contribute positively to stage efficiency.

show abstract

Non-reactive test rig for combustor-turbine interaction studies in industrial gas turbines

Fiorineschi

Bacci

Frillici

et al. 2021

JEDT

View full text Add to dashboard Cite

Purpose This paper aims to present the design of a particular non-reactive test rig for combustion swirlers and first stage turbine nozzles. The test rig is required for important experimental activities aimed at the optimization of a specific class of gas turbines. Design/methodology/approach A multi-disciplinary team performed the design process by following a tailored design approach, which has been developed for the specific case. The design outcomes allowed to build a fully functional test rig to be introduced in a test cell and then to perform preliminary experiments about the fluid dynamic behaviour of the turbine elements. Findings The followed design approach allowed to efficiently perform the task, by supporting the information exchange among the different subjects involved in both the conceptual and the embodiment design of the test rig. Additionally, the performed experiments allowed to achieve a final configuration that makes the test rig a valuable test case for combustor-turbine interaction studies. Research limitations/implications The study described in this paper is focused on the design of a specific test rig, used for first validation tests. However, the achieved results (both in terms of design and test) constitutes the underpinning of the in-depth investigations to be performed in the next steps of the experimental campaign. Originality/value To the best of the authors’ knowledge, the present paper is the first one that comprehensively describes the design activity of an experimental test rig for turbine application, also providing indications about the specific methodological procedure used to manage the process.

show abstract

The LEMCOTEC 1½ Stage Film-Cooled HP Turbine: Design, Integration and Testing in the Oxford Turbine Research Facility

Cited by 6 publications

References 16 publications

Effect of a Combined Hot-Streak and Swirl Profile on Cooled 1.5-Stage Turbine Aerodynamics: An Experimental and Computational Study

Effect of a Combined Hot-Streak and Swirl Profile on Cooled 1.5-Stage Turbine Aerodynamics: An Experimental and Computational Study

Impact of Rotor-Casing Effusion Cooling on Turbine Performance and Operating Point: An Experimental, Computational, and Theoretical Study

Non-reactive test rig for combustor-turbine interaction studies in industrial gas turbines

Contact Info

Product

Resources

About