Pilot study for modelling gas turbine component behaviour: Part VI: Inventory of material and lifing models

The lifing of gas turbine components is a complex process. It entails a number of modelling steps in which various disciplines are involved. The current work provides information relevant to the determination of the stress and strain distributions in a component, and the evaluation of these distributions in terms of a relevant material model....

Materiaalkeuze voor vliegende gasturbines

Het gebruik van non-ferrometaien in de fieetste delen van straalmotoren spreekt vanzelf. In compressoren van straalmotoren - met temperaturen tot 600 °C - worden echter zowel ijzerlegeringen als non-ferrometaien gebruikt. Op grond van mectianisctie eigensctiappen en gewicht verdienen titanium- en nikkel-legeringen hier de voorkeur. Dat er toch...

Gas turbine compressor corrosion and erosion in Western Europe

It is shown that for gas turbines in the West European environment: * during of)eration hygroscopic salts - notably ammonium sulphate (originating from manure) and sodium and magnesium chloride (from sea salt) - are deposited on compressor components. * during shutdowns these wet deposits acidify owing to the absorption of the air pollutants NO2...

Stress corrosion resistance of damage tolerant aluminium-lithium sheet materials

The SCC resistances of three damage tolerant aluminium sheet materials were determined by means of the ASCOR (Automated Stress Corrosion Ring) test. The conventional damage tolerant sheet material 2024-T3 was used as reference. The sec resistance of 8090-T81 turned out to be only slightly lower than the sec resistance of 2024-T3. In contrast,...

Stress corrosion resistance of damage tolerant aluminium-lithium sheet materials

The SCC resistances of three damage tolerant aluminium sheet materials were determined by means of the ASCOR (Automated Stress COrrosion Ring) test. The conventional damage tolerant sheet material 2024-T3 was used as reference. The SCC resistance of 8090-T81 turned out to be only slightly lower than the SCC resistance of 2024-T3. In contrast,...

Wasmiddelen voor gasturbines vallen vies tegen

Deposits are regularly removed from compressor blades and vanes of installed jet engines and gas turbines by compressor washing. Hereby a compressor cleaner is sprayed into the compressor while operating at reduced or normal r.p.m. Recently developed compressor cleaners are claimed to be ecologically sound. In addition, many new compressor...

Additional investigation on the AL-Li plate alloy DTD XXXA-T651 (AA 8090-T651)

One of the first commercially available Al-Li plate alloys, DTD XXXA-T651, produced by ALCAN International Ltd., was tested in the framework of a European cooperative programme (GARTEUR). The engineering properties were determined in a previous investigation. The present report describes the results of an additional investigation with respect to...

New erosion resistant compressor coatings

Airfoils of gas turbines and jet engines frequently deteriorate by erosion or corrosion: Protection can be offered by special coatings that are resistant to either erosion or corrosion. However, the conventional corrosion resistant compressor coatings have very poor erosion resistance. Therefore there is a tendency to apply compressor coatings...

Rinsing water analysis of helicopter jet engine compressors

Advanced aluminium alloy plate materials for damage tolerant aircraft structures

Engineering properties of the recently developed plate alloy 2324-T39 and the conventional alloy 2024-T351 are compared. Some results for the aluminium-lithium alloy DTD XXXA-T651 (Aluminium Association designation 8090) are also included. The strengths of 2324-T39 and DTD XXXA-T651 were comparable and significantly higher than that of 2024-T351...

Creep, fatigue and their interaction in coated and uncoated René 80

The effects of coating (with Codep B) and of creep-fatigue interactions on creep and fatigue properties of the turbine blade material René 80 at 900 °C were investigated. Coating reduced the high cycle fatigue life because of crack initiation at brittle particles in the coating. This process played no role for creep, where crack initiation took...

Microstructural and fractographic analysis of fatigue crack propagation in 2024-T351 and 2324-T39

Differences in the fatigue crack propagation rates of 2024-T351 and 2324-T39 are explicable from differences in microstructures. The slope changes (transitions) in the crack propagation curves are probably associated with the plastic zone sizes being equal to certain microstructural dimensions. As a consequence of different chemical compostion...

Effect of cooling rate on corrosion properties and microstructure of high strength aluminium alloys

The Jominy end-quench test was applied to rods of the alximinium alloys T010 and X TO9I to obtain a decreasing cooling rate over the length of the rods. After heat treating to a high strength T6 and an overaged TT condition the corrosion properties and the microstructure were determined related to the cooling rate. No influence of cooling rate...

Effect of penetrant on fatigue of aluminium alloy lap joints

The effect of penetrant on the fatigue life of single shear riveted lap joints was investigated by flight simulation fatigue tests using the MINITWIST gust spectrum. The penetrant/material combination investigated was ARDROX 985 P3T and aluminium alloy 202U-T3 sheet material (both bare and clad) respectively. The effect of penetrant on the...

Coarsening and solutioning of precipitates in superalloys

Coarsening and solutioning of the main strengthening phase for the majority of superalloys, the y' phase, are discussed. It is shown that a general prediction of coarsening rates and solutioning temperatures is possible.

The Jominy end-quench test for investigation of corrosion properties and microstructure of high strength aluminium alloys

The Jominy end-quench test was applied to extruded rods of the aluminium alloys 2024 and 7075 to obtain a decreasing quench rate over the length of the rods. Subsequently the alloys were heat treated to the conditions: 2024-T4, 2024-T6, 7075-T73. A corrosion investigation and a transmission electron microscopy investigation were performed to...