Aerospace Research - ISTC Funded Projects 1994-2009

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Background Propeller driven aviation (helicopters, turboprop airplanes, compound helicopters) is still essential for transportation needs. A rotor, having changeable diameter or geometry of blades during operation, is determined as the variablegeometry rotor (VGR). Development of rotors with variable diameter and blade twist during flight is a promising research direction. A rotor with fixed geometry is a result of compromise between requirements of regimes of takeoff and high speed in cruise flight. Takeoff is optimal at the large diameter and small twist and cruise flight is optimal at the small diameter and large twist. The optimality is in large payload capacity at takeoff and high maximum speed of cruise flight, which can be provided by VGR. The VGR is effective both for helicopters and airplanes. However, the VGR is especially effective for the airplanes with vertical takeoff and landing (VTOL) in the both regimes (takeoff and cruise flight). The idea of VGR application is not a new one. There are patents with various schemes of rotor diameter changing, but they suggest very complex technical solutions not applicable Enhancement of Flight Performance, Economy and Efficiency nowadays. Thus, the problem of VGR has not been solved yet. In the USA, the Boeing Company concentrated on the problem of rotor blade twist, whereas the Sikorsky Company investigated the variable diameter rotor concept. Project Objectives The objective of this project was to develop and create a prototype of a variablegeometry propeller for vertical and fast takeoff airplanes. Description of the Work This is a feasibility stage of an initial full project aimed at creation of a prototype of a variablegeometry propeller for vertical and fast takeoff airplanes. Obtained Results Scientific and experimental approaches suggested for the accomplishment of Project objectives have been substantiated. A Georgian patent was filed: GE P I844B of May 8, I999 for invention of “Control Device of the Variable Geometry Rotor,” authored by S.Khutsishvili. 89
90 Aerospace Research. Volume 1 Number: #G-060-2 Full and Short Title: Variable Geometry Propeller (VGP) and Actuating Means (Actuating Components) Variable Geometry Propeller Tech Code/Area/Field: SATAER/Space, Aircraft and Surface Transportation/Aeronautics Status: Project completed Technology Development Phase: Technology development Allocated Funding: $289,529 (US) Commencement date: (starting date) April 1, 2000 Duration: 30 months Leading Institute: Georgian Technical University, Tbilisi, Georgia Contact Information: Phone: +995 (32) 940052; 332329, 943716, fax: +995 (32) 942033; 9437I6, email: inform@gtu.edu.ge Supporting Institutes: No Collaborators: Boeing Defense & Space Group, Philadelphia, PA, USA (Dadone L) Project Manager: TURMANIDZE Raul Contact Information: Phone: +995 (32) 940052; 332329; 943716, fax: +995 (32) 942033, 9437I6, email: inform@gtu.edu.ge ISTC Senior Project Manager: TYURIN Igor Contact Information: Phone: +7 (495) 9823196, fax: +7 (499) 9783603, email: tyurin@ istc.ru ISTC Website: http://www.istc.ru Background Propeller driven aviation (helicopters, turboprop airplanes, compound helicopters) is still essential for transportation needs. A rotor, having changeable diameter or geometry of blades during operation, is determined as the variablegeometry rotor (VGR). Development of rotors with variable diameter and blade twist during flight is a promising research direction. Project Objectives The objectives of the Project were to investigate and develop a rotor with variable diameter, pitch, blade twist, and actuators. Description of the Work The work on designing and fabrication of the VGR and a test stand were performed. The rotor was developed step by step. Initially, a model of the VGR was designed and
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INTERNATIONAL SCIENCE AND TECHNOLOG
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The International Science and Techn
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ISTC Programs The core ISTC program
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Research Projects in Aeronautics To
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Contents Aeronautics Enhancement of
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Background Laminar-turbulent transi
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spectra filling in the laminarto
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Project Number: #0199 Enhancement o
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length to the distance between them
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the maximal intensity was found to
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Comparison of weight chara cteristi
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of TWT walls was simulated within t
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An integrated analysis was made by
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Background Development of modern tu
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Description of the Work The experim
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The aim of the project was to inves
Page 40 and 41: - lower skin and stringers (titaniu
Page 42 and 43: Number: #0808 Enhancement of Flight
Page 44 and 45: opportunities for creating novel hy
Page 46 and 47: Unfortunately, with the computation
Page 48 and 49: Number: #0887 Enhancement of Flight
Page 50 and 51: along with a flow rate approaching
Page 52 and 53: with a conical nozzle failed to obt
Page 54 and 55: Bleed of the boundary layer on the
Page 56 and 57: Project Number: #0935 Enhancement o
Page 58 and 59: Description of the Work Within the
Page 60 and 61: Obtained Results The following resu
Page 62 and 63: Project Objectives The objective of
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Page 68 and 69: Description of the Work The followi
Page 70 and 71: turbulent boundary layers and bound
Page 74 and 75: Enhancement of Flight Performance,
Page 76 and 77: computational grid adapted to a WT
Page 78 and 79: possessing metrological parameters
Page 80 and 81: • a study of nonsymmetrical crack
Page 82 and 83: For example, freeplay can arise i
Page 84 and 85: nonlinearities and uncertainties. T
Page 86 and 87: een found. Research of interference
Page 88 and 89: verification of numerical codes des
Page 92 and 93: fabricated. Thereafter, a model of
Page 94 and 95: Number: #G-0916 Enhancement of Flig
Page 96 and 97: Number: #G-1600 Enhancement of Flig
Page 98 and 99: Improvement of Safety and Operation
Page 100 and 101: harmonics of the mass defect and th
Page 102 and 103: important for the HRG, are not meas
Page 104 and 105: Project Number: #0201 Improvement o
Page 106 and 107: Numerical matching at the zone boun
Page 108 and 109: The time history (for a time interv
Page 110 and 111: ISTC Project #101898 “Flight sa
Page 112 and 113: In recent years, remote sounding of
Page 114 and 115: at a distance of 1020 wingspans u
Page 116 and 117: Engineering (VORTSEC) and simplifie
Page 118 and 119: this type, a sample (aircraft) is a
Page 120 and 121: simulated. The impactorsimulator
Page 122 and 123: Decrease of Environmental Impact Pr
Page 124 and 125: The analysis of flow fields in the
Page 126 and 127: Ozone layer impact Combustion produ
Page 128 and 129: Number: #0497 Decrease of Environme
Page 130 and 131: • almost all the air and fuel (ex
Page 132 and 133: Project Number: #0627 Decrease of E
Page 134 and 135: Number: #0627.2 Decrease of Environ
Page 136 and 137: to a gasgenerator airplane in a p
Page 138 and 139: Project Objectives The objective of
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Project Number: #2249 Decrease of E
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In a new Project, this code was fur
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Obtained Results The following main
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Project Objectives The objectives o
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• for the flying test bed Tu154
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Recently, a number of papers on low
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Obtained Results 1. A model combust
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Institutes - ISTC Recipients in Aer
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List of the Project Proposals (open
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List of the Project Proposals (open
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Aerospace Research - ISTC Funded Projects 1994-2009

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