Design and Testing of a Rig to Investigate Buoyancy-Induced Heat Transfer in Aero-Engine Compressor Rotors

A calculate method based on ε-NTU model for heat transfer characteristics of shell-tube fuel-cooled heat exchanger of aero-engine lubrication system was built. The heat convection coefficient was obtained by a dimensionless curve (Re~StPr2/3), which was detailed introduced as well. A case study was executed at last. The absolute error of the outlet lubrication of the tube side and the shell side between the value of calculation and experiment was less than ±10°C, and the relative error was less than 6.5%. The absolute error of the heat transferred between calculation and experiment was less than ±0.9kW, and the relative error was less than 7.4%. It indicates that the mothod is available for the investigation of heat transfer characteristics of shell-tube fuel-cooled heat exchanger.

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Oxidation-Resistance of (Ti,Al,Cr,Y)N Coatings Prepared by Arc Ion Plating

Advanced Materials Research ◽

10.4028/www.scientific.net/amr.177.338 ◽

2010 ◽

Vol 177 ◽

pp. 338-341

Author(s):

Ming Sheng Li ◽

Yong Zhong Fan ◽

Shu Juan Zhang

Keyword(s):

Oxidation Resistance ◽

Crystal Size ◽

Substrate Bias ◽

Compressor Blades ◽

Arc Ion Plating ◽

Ion Plating ◽

Cr Content ◽

Heat Treated ◽

Aero Engine ◽

Engine Compressor

In this study, composite metastable (Ti0.49Al0.49Y0.02)N, (Ti0.44Al0.44Cr0.1Y0.02)N and (Ti0.34Al0.34Cr0.3Y0.02)N coatings were respectively deposited on a wrought martensite steel 1Cr11Ni2W2MoV for aero-engine compressor blades by arc ion plating technique with a pulse substrate bias. All the coatings have B1NaCl phase structure with a (220) preferred orientation and dense structures. The introduction of chromium into the coatings gave rise to a minute shrinkage of crystal lattice and a decrease of crystal size. Annealed at 800°C, Oxidation-resistance of the coatings improved with increased Cr content. But heat-treated at 900°C, the incorporation of Cr gave rise to obvious decrease of oxidation-resistance.

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Second Paper: Experiments on a Transpiration Cooled Combustion Chamber

Proceedings of the Institution of Mechanical Engineers ◽

10.1243/pime_proc_1973_187_096_02 ◽

1973 ◽

Vol 187 (1) ◽

pp. 158-169 ◽

Cited By ~ 2

Author(s):

F. J. Bayley ◽

J. W. Cornforth ◽

A. B. Turner

Keyword(s):

Heat Transfer ◽

Static Pressure ◽

Porous Metal ◽

Cooling Efficiency ◽

Combustion Chambers ◽

Flame Tube ◽

Coolant Injection ◽

Drop Mass ◽

Theoretical Predictions ◽

Design And Testing

The first part of an experimental and theoretical investigation into the feasibility of transpiration cooled combustion chambers is discussed, as well as the design and testing of two Rolls-Royce ‘Dart’ porous flame tubes. The theory of heat transfer in porous materials is briefly described and correlations for heat transfer and pressure drop-mass flow are presented for selected samples of porous metal. Experimental results are presented in which the cooling efficiency of the original ‘Dart’ splash-cooled flame tube is compared with two porous replacements constructed from sintered woven wire porous metal compacts having different permeabilities. Tests were conducted at 1 and 4 atm pressure and some selected results are compared with theoretical predictions made with and without account being taken of the effect of coolant injection on the convective heat flux. The high effectiveness of transpiration cooling is clearly demonstrated but it is also shown that the distribution of static pressure in the annulus formed between the flame tube and the casing, both longitudinally and circumferentially, plays a very important part in the design of a porous flame tube.

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FEA on vibration characteristics analysis of an aero-engine compressor blade

2012 24th Chinese Control and Decision Conference (CCDC) ◽

10.1109/ccdc.2012.6243083 ◽

2012 ◽

Author(s):

Weiqiang Zhao ◽

Yongxian Liu ◽

Mowu Lu ◽

Qingjun Guo

Keyword(s):

Compressor Blade ◽

Vibration Characteristics ◽

Aero Engine ◽

Characteristics Analysis ◽

Engine Compressor

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Preliminary Optimization of Multi-Stage Axial-Flow Industrial Process Compressors Using Aero-Engine Compressor Design Strategy

Applied Sciences ◽

10.3390/app11199248 ◽

2021 ◽

Vol 11 (19) ◽

pp. 9248

Author(s):

Fan Lei ◽

Chuhua Zhang

Keyword(s):

Optimal Design ◽

Gas Turbines ◽

Design Method ◽

Industrial Process ◽

Design Strategy ◽

Preliminary Design ◽

Stage Design ◽

Compressor Design ◽

Aero Engine ◽

Engine Compressor

Aero-engine core compressor preliminary design strategy has been successfully applied to the advanced design of gas turbines compressors. However, few researchers have addressed the application of the aero-engine core compressor preliminary design strategy in the preliminary optimal design of industrial process compressors. Here we embedded the aero-engine core compressor preliminary design strategy into a preliminary optimal design method, in which six types of design parameters widely used to define the aero-engine compressor configuration, i.e., aspect ratio, solidity, reaction, rotation speed, outlet axial Mach number, and inlet radius ratio, were used as the design variables. The 4-stage, 5-stage, 6-stage, and 7-stage compressor configuration with the same overall design requirements for a large-scale air separation main compressor were preliminarily optimized by the developed method, in which the 4-stage design has a stage pressure rise level of current aero-engine core compressors, whereas the 7-stage design has that of current industrial process compressors. The optimized compressor configurations were then refined with the throughflow-based detailed design method and finally verified with computational fluid dynamic simulations. It is found that the developed method can optimize design efficiency and accurately predict aerodynamic performance of compressors in a few minutes. Several design guidelines for the advanced industrial process compressors were also identified. This work is of significance in extending aero-engine core compressor design strategy to the design of advanced industrial process compressors.

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Numerical Study on Film Effectiveness and Heat Transfer Characteristics of Aero-Engine Nose Cone With Hot Air Film

Volume 7B: Heat Transfer ◽

10.1115/gt2020-14649 ◽

2020 ◽

Author(s):

Tao Yang ◽

Li Zhang ◽

Hui-Ren Zhu ◽

Xing-Ming Wang

Keyword(s):

Heat Transfer ◽

Numerical Study ◽

Windward Side ◽

Heat Transfer Characteristics ◽

Hole Shape ◽

Blowing Ratio ◽

Transfer Characteristics ◽

Aero Engine ◽

Nose Cone ◽

Hot Film

Abstract When the aircraft works in an environment containing supercooled water droplets, it is easy to cause the engine inlet nose cone on the windward side to freeze, which not only affects the performance of the engine, but also leads to flight accidents. Therefore, it is necessary to research the anti-icing technology of aero-engine nose cone components. At present, the air intake cone of the aircraft mainly forms a thermal anti-icing system by means of hot film anti-icing and heating impingement anti-icing. In this paper, the effects of blowing ratio, film hole pitch, hole shape and film hole arrangement method on film heating effectiveness and heat transfer characteristics are studied by numerical simulation methods for the hot film anti-icing system of the nose cone. The results show that with the increase of the blowing ratio, the film heating effectiveness in the downstream area quickly decreases first and then increases, and the range of change aggrandizes. Under the given condition, as the pitch between the film holes decreases, the area covered by the film extends, and the heating effectiveness improves significantly. In the case of high blowing ratio, the advantage of film heating effectiveness of waist-shaped film hole is more apparent. The laterally-averaged film heating effectiveness of the staggered film holes is much higher than that of the aligned film holes. For the characteristics of film heat transfer, the hole pitch and hole shape has little effect on the heat transfer characteristics at low blowing ratio. In the case of high blowing ratio, the heat transfer effect will be greatly weakened when the hole pitch is increased, moreover the heat transfer efficiency of the waist-shaped hole is better. In the region near the exit of the secondary row film hole, the heat transfer characteristics of the staggered structure is stronger than that in the aligned structure. In addition, it is found that the high heat transfer region for staggered arrangement shows W–shaped.

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Design and Testing of a Rig to Investigate Buoyancy-Induced Heat Transfer in Aero-Engine Compressor Rotors

Volume 7C: Heat Transfer ◽

10.1115/gt2020-14422 ◽

2020 ◽

Author(s):

Dario Luberti ◽

Marios Patinios ◽

Richard W. Jackson ◽

Hui Tang ◽

Oliver J. Pountney ◽

...

Keyword(s):

Heat Transfer ◽

Radial Distribution ◽

Tip Clearance ◽

Heat Transfer Analysis ◽

Radiant Heat Transfer ◽

Central Cavity ◽

Engine Operation ◽

Closed Cavity ◽

Rotating Discs ◽

Aero Engine

Abstract The change in compressor blade-tip clearance across the flight cycle depends on the expansion of the rotor, which in turn depends on the temperature and stress in the discs. The radial distribution of temperature is directly coupled to the buoyancy-driven flow and heat transfer in the rotating disc cavities. This paper describes a new test rig specifically designed to investigate this conjugate phenomenon. The rig test section includes four rotating discs enclosing three cavities. Two discs in the central cavity are instrumented with thermocouples to provide the radial distribution of temperature; the two outer cavities are thermally insulated to create appropriate boundary conditions for the heat transfer analysis. An axial throughflow of air is supplied between a stationary shaft and the bore of the discs. The temperature of the throughflow air is measured by thermocouples in rakes upstream and downstream of the central cavity. For a cold throughflow, the outer shroud of the central cavity is heated. Two independently-controlled radiant heaters allow differential shroud temperatures for the upstream and downstream discs, as found in aero-engine compressors. Alternatively, the throughflow can be heated above the shroud temperature to simulate the transient conditions during engine operation where stratified flow can occur inside the cavity. The rig is designed to operate in conditions where both convective and radiative heat transfer dominate; all internal surfaces of the cavity are painted matt black to allow the accurate calculation of the radiant heat transfer. Separate attachments can be fitted to the cobs of both central discs; the attachments reduce the axial gap between the cobs — reducing the gap to zero creates a closed cavity, which can occur in some compressor designs. Other instrumentation includes heat-flux gauges on the shroud and high-frequency pressure transducers embedded into the disc diaphragm to capture unsteady flow structures. Attention has been given to experimental uncertainty, including the computation of the thermal-disturbance errors, caused by thermocouples embedded in the rotating discs; a Bayesian statistical model is used to reduce the effect of uncertainties in temperature measurements on the calculation of the Nusselt number. The effect of relevant non-dimensional parameters on the radial distribution of the disc and throughflow temperatures has been shown for some typical cases.

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Influences of the Geometry of the Scavenge Pipe on the Air–Oil Two-Phase Flow and Heat Transfer in an Aero-Engine Bearing Chamber

ACS Omega ◽

10.1021/acsomega.9b02095 ◽

2019 ◽

Vol 4 (12) ◽

pp. 15226-15233 ◽

Cited By ~ 1

Author(s):

Peng Lu ◽

Lulu Fang ◽

Xiangyang Wang ◽

Qihang Ye ◽

Jingzhou Zhang

Keyword(s):

Heat Transfer ◽

Two Phase Flow ◽

Phase Flow ◽

Two Phase ◽

Flow And Heat Transfer ◽

Aero Engine ◽

Engine Bearing

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Measurement and Analysis of Buoyancy-Induced Heat Transfer in Aero-Engine Compressor Rotors

Journal of Engineering for Gas Turbines and Power ◽

10.1115/1.4049100 ◽

2020 ◽

Author(s):

Richard Jackson ◽

Dario Luberti ◽

Hui Tang ◽

Oliver J Pountney ◽

James Scobie ◽

...

Keyword(s):

Heat Transfer ◽

Three Dimensional ◽

Conjugate Problem ◽

Radial Temperature ◽

Thermal Boundary Conditions ◽

Nusselt Numbers ◽

First Results ◽

Engine Compressor ◽

Induced Flow ◽

Aero Engines

Abstract The flow inside cavities between co-rotating compressor discs of aero-engines is driven by buoyancy, with Grashof numbers exceeding 1013. This phenomenon creates a conjugate problem: the Nusselt numbers depend on the radial temperature distribution of the discs, and the disc temperatures depend on the Nusselt numbers. Furthermore, Coriolis forces in the rotating fluid generate cyclonic and anti-cyclonic circulations inside the cavity. Such flows are three-dimensional, unsteady and unstable, and it is a challenge to compute and measure the heat transfer from the discs to the axial throughflow in the compressor. In this paper, Nusselt numbers are experimentally determined from measurements of steady-state temperatures on the surfaces of both discs in a rotating cavity of the Bath Compressor-Cavity Rig. The data are collected over a range of engine-representative parameters and are the first results from a new experimental facility specifically designed to investigate buoyancy-induced flow. The radial distributions of disc temperature were collected under carefully-controlled thermal boundary conditions appropriate for analysis using a Bayesian model combined with the equations for a circular fin. The Owen-Tang buoyancy model has been used to compare predicted radial distributions of disc temperatures and Nusselt numbers with some of the experimentally determined values, taking account of radiation between the interior surfaces of the cavity. The experiments show that the average Nusselt numbers on the disc increase as the buoyancy forces increase. At high rotational speeds the temperature rise in the core, created by compressibility effects in

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