The Design, Performance and Analysis of a High Work Capacity Transonic Turbine

Bryce, J. D.; Litchfield, M. R.; Leversuch, N. P.

doi:10.1115/1.3239838

Cited by 10 publications

(5 citation statements)

References 6 publications

(7 reference statements)

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“…Crow et al [5] (Energy Efficient Engine Programme) observed in an uncooled single stage that at constant pressure ratio, 4 per cent increase in the degree of reaction resulted in a 0.8 per cent increase in efficiency (measured by the thermodynamic method). Bryce et al [6] (Royal Aircraft Establishment) tested a highly loaded stage ( H /U 2 = 2.1) with a vane exit Mach number of 1.30 obtaining an adiabatic efficiency of 87 per cent. Moustapha et al [7] (Highly Loaded Turbine) showed the effect of blade loading on high loaded ( H /U 2 = 2.4) stage efficiency at off-design conditions; increase in the rotor blade loading by 53 per cent reduced the efficiency by 2.5 per cent.…”

Section: Introductionmentioning

confidence: 99%

Performance analysis of a transonic high-pressure turbine

Yasa

Paniagua

Bussolin³

2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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Efficiency is a crucial design parameter in any turbine development. This research presents a detailed investigation on the efficiency of a modern transonic high-pressure turbine. The work focuses on the study of the efficiency loss at different stage loading factors (ranging from H /U 2 = 1.3 to 2.7) and various flow factors (V ax /U = 0.41 to 0.90). In particular, the present research is of utmost importance to understand the effect of the vane trailing edge shocks in the turbine stage efficiency.The experimental work was carried out in a compression tube facility that allows testing of the turbine at temperature ratios, Re and Mach numbers, encountered in real engines. The efficiency is measured by the mechanical method. Experiments were performed with two different vanes (cooled and uncooled) at two stagger angles, four rotational speeds (4570-6500 r/min) and three pressure ratios (p 01 /p s3 ranging from 2.42 to 5.12). The effect of the change of reaction and rotor incidence is correlated with the performance. Three-dimensional Navier-Stokes calculations aid the interpretation of the results.

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Section: Introductionmentioning

confidence: 99%

Performance analysis of a transonic high-pressure turbine

Yasa

Paniagua

Bussolin³

2007

Proceedings of the Institution of Mechanical Engineers, Part A:

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“…increase from 4 to 5.5 for E 3 (Crow et al, 1980) and only 0.7% for a P.R. increase from 4.5 to 5.2 for RAE (Bryce et al, 1985). The characteristics of the HWRT stage (Table 1), and in particular the rotor trailing edge blockage and stage reaction, are the reason for this rapid drop in efficiency.…”

Section: Design and Off-design Performance Of The Uncooled Turbinementioning

confidence: 96%

“…They demonstrated 90.3% uncooled Presented at the International Gas Turbine and Aeroengine Congress & Exposition Houston, Texas -June 5-8, 1995 This paper has been accepted for publication in the Transactions of the ASME Discussion of it will be accepted at ASME Headquarters until September 30,1995 efficiency at a reaction of 35% and an efficiency drop of 2.5% because of cooling. Bryce et al (1985) investigated the performance of a turbine with a P.R. of 4.5, a OH/U2 of 2.1 and a hub-to-tip diameter ratio of 0.84 (RAE in Fig.…”

Section: Introductionmentioning

confidence: 99%

The Design and Performance of a High Work Research Turbine

Vlasic¹,

Girgis²,

Moustapha³

1995

Volume 1: Turbomachinery

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This paper describes the design and performance of a high work single stage research turbine with a pressure ratio of 5.0, a stage loading of 2.2 and cooled stator and rotor. Tests were carried out in a cold flow rig and as part of a gas generator facility. The performance of the turbine was assessed, through measurements of reaction, rotor exit conditions and efficiency, with and without airfoil cooling. The measured cooled efficiency in the cold rig was 79.9%, which, after correcting for temperature and measuring plane location, matched reasonably well the efficiency of 81.5% in the gas generator test. The effect of cooling, as measured in the cold rig, was to reduce the turbine efficiency by 2.1%. A part load turbine map was obtained at 100, 110 and 118% design speed and at 3.9, 5.0 and 6.0 pressure ratio. The influence of speed and the limit load pattern for transonic turbines are discussed. The effect of the downstream measuring distance on the calculated efficiency was determined using three different locations. An efficiency drop of 3.2% was measured between the rotor trailing edge plane and a distance four chords downstream.

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“…Ori_Case1 from a turbine institute has not been published. Ori_Case2 is from (Bryce et al 1985). Ori_Case3 and Ori_Case4 are from (Behr 2007).…”

Section: Application Of the Proposed Policy Modelmentioning

confidence: 99%

A Data-Based Policy Model for Intelligent Turbine Cascade Design

2022

JAFM

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The study of intelligent design methods is becoming a hot topic for the design of turbine cascades. This paper proposes a data-based policy model to achieve intelligent design. To gain a high-quality policy model, empirical equations and "space extending + elitism" are adopted to dynamically optimize database. This guarantees the quality of the model. Compared to traditional optimization design approaches, the proposed method relies on less human experience to design a turbine cascade. Ten different turbine cascades are used to verify this method. Results show that, aerodynamic performance of the cascades redesigned is either the same as or better than that of the traditional cascades. The computing time is reduced by more than one order of magnitude compared to a "CFD + optimization algorithm" or "surrogate model + optimization algorithm" method. With the advantages in computing time and intelligence, the proposed novel method shows the possibility of replacing traditional design methods.

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The Design, Performance and Analysis of a High Work Capacity Transonic Turbine

Cited by 10 publications

References 6 publications

Performance analysis of a transonic high-pressure turbine

Performance analysis of a transonic high-pressure turbine

The Design and Performance of a High Work Research Turbine

A Data-Based Policy Model for Intelligent Turbine Cascade Design

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