Integrated lifing analysis of a film-cooled turbine blade

A method to predict gas turbine component life based on engine performance analysis is demonstrated on a hot section gas turbine component. The mechanical and thermal loading of the first stage high pressure turbine rotor blade of the FlOO-PW-220 engine, one of the most severely loaded components in the engine, is analyzed and a life assessment...

Analysis of combined convective and film cooling on an existing turbine blade

To support gas turbine operators, NLR is developing capabilities for life assessment of hot engine components. As a typical example the first rotor blades of the high pressure (HP) turbine of the FlOO- PW-220 military turbofan will be discussed. For these blades tools have been developed to derive the blade temperature history from flight data...

Pilot study for modelling gas turbine component behaviour: Part VII: Inventory of European activities (summary of AGARD publications)

In order to position the activities at NLR on the hot flow modelling and testing of gas turbine components a survey has been made of current activities in Europe outside the Netherlands. The present report is confined to activities on turbine blades and vanes because this has the first priority at NLR, considering the national market (blade life...

Engine flow simulation for wind tunnels testing at NLR

A review is presented of the engine flow simulation techniques for wind tunnel testing at NLR. In particular the techniques for turbofan engine simulation will be discussed like the blown nacelle and the turbo powered simulator. Also some remarks will be made on propeller model test techniques at NLR.

Aerodynamisch geluid van windturbines

In deze voordracht wordt een overzicht gegeven van het door het NLR uitgevoerde onderzoek met betrekking tot het aërodynamisch gegenereerde geluid van windturbines met horizontale as en de rotor bovenwinds van de toren. Op grond van literatuuronderzoek is een globale predictiemethode geformuleerd. Daarnaast wordt een meer gedetailleerd...

Recente ontwikkelingen in de voortstuwingsaerodynamica

Lezing gehouden tijdens het NVvL-VSV Symposium 'Recente ontwikkelingen op Aërodynamisch gebied' op vrijdag 26 april 1985 in Delft.

Aeroacoustic research in the Netherlands related to aircraft development

This paper reviews the acoustic research carried out in the past 10 years by Fokker and NLR to support the aircraft development programmes in the Netherlands. The following subjects are highlighted, emphasizing the development of the necessary experimental techniques and design tools. For jet noise reduction the feasibility of a lined ejector...

Voorstel voor experimenteel ondezoek fan-lawaai

The engine/airframe interference drag at cruise conditions using propulsion simulation

A wind tunnel test procedure is described to determine from the thrust minus drag measurements the aircraft drag and engine/airframe interference drag at cruise conditions. The definitions of the thrust and drag terms in use are given. Engine thrust simulation is provided by a calibrated Turbofan Powered Simulator (TPS). Further the use of a...

Comparison of hot and cold subsonic jets in an external flow with reference to jet engine simulation

An experimental investigation was carried out concerning the effect of jet heating and external flow on the mean flow properties of a subsonic jet. A 60 mm diameter jet was tested in a wind tunnel at wind speeds of 0 and 60 m/s. Jet mach numbers varied between O.44 and 0.94 and jet total temperatures were 310 and 86O K. Velocity and temperature...

Mogelijkheden voor aero-akoestisch onderzoek in de LST 8x6

In dit rapport wordt nagegaan wat de mogelijkheden zijn om in de ontworpen lage-snelheidswindtunnel LST 8x6 van het NLR aero-akoestisch onderzoek te verrichten . Het blijkt dat hiervoor een aantal extra voorzieningen nodig zijn, te weten: - een open meetplaatsoonfiguratie, - bekleden van de hoeksohoepen met geluidsahsorherend materiaalt -...

Facilities for aerodynamic testing at hypersonic speeds

An assessment i s made of the usefulness and potential of existing European Tiypersonic facilities, on the basis of the planned U.3, space shuttleproject and a hypothetical hypersonic transport aircraft. With respect to aerodynamic testing of space shuttle type of vehicle it is pointed out that a significant gap exists between M=10 and M=15. At...

Specificatie voor en keuze van een hypersone installatie voor het NLR

Aerodynamisch ontwerp voor een hypersone guntunnel