High Temperature Capability – Compressor and Discs (SILOET II Project 6)

One of the key ways to improve the specific fuel consumption (sfc) and reduce the environmental impact of aero engines is to increase the thermal efficiency of the engine. This can be achieved by higher pressure ratios and operating temperatures. To meet these requirements, improved compressor efficiency is one of the key requirements.

The project consisted of 4 work packages focusing on different aspects of high temperature compressor technologies:

• Increasing the temperature capability of axial compressors through design and improved aerofoil materials to enable a compressor to have adequate design life with exit temperatures in excess of 700°C
• Development of robust methods for the manufacture of abradable liners; tipping of blisks, blades and fins with abrasive materials to improve compressor sealing, reduce leakage and improve fuel burn
• Development of a high-temperature, high-strength, single piece shaft steel with a temperature capability of 475°C, which will eliminate welds, reduced manufacturing cost and reduce the weight of the shaft and engine
• Demonstrate increased temperature capability of the latest high temperature disc material, RR1000, which will reduce sfc and increase the useable life of critical parts

Download the High Temperature Capability – Compressor and Discs (SILOET II Project 6) case study
Short Title: SILOET 2 P6
Project Number: 110120
Project Cost: £9,900,000
End Date: 30th Jun 2016
Time Horizon: Secure
Lead Partner: Rolls-Royce PLC
Attributes: Fuel Efficiency
ATI Value Stream: Propulsion of the future