Accession Number : ADP006202
Title : Advanced Techniques Employed in Blade Cooling Research,
Corporate Author : ROLLS-ROYCE LTD BRISTOL (UNITED KINGDOM)
Personal Author(s) : Rogers, H. E. ; Graham, C. ; McNicholas, K.
Report Date : SEP 1987
Pagination or Media Count : 13
Abstract : As the demand for improved performance of advanced gas turbine engine components continues, the environment within an engine, in which the turbine must operate, has become more hostile. The operating temperatures of turbines have increased such that not only the first stage, but in many cases the second stage requires some form of cooling. The design of an advanced cooling system for moderately cooled second stage blades was undertaken as part of a demonstrator project. The design process, involving complex computer modelling, and hot rig testing of the blades, is described in part 1 of this paper. The test results confirmed that substantial increases in cooling efficiency can be gained by introducing small scale turbulators into radial hole cooling systems. Part 2 describes a development temperature measurement technique based on a video camera operating in the near infra-red region. The results of the video pyrometry were validated from results obtained from a series of demonstrator hot rig tests. Also discussed are a number of problems relating to surface temperature measurement, in particular, the method used to achieve artificially matured blade surfaces.
Descriptors : *GAS TURBINES, *TURBINE COMPONENTS, COOLANTS, ROTOR BLADES, RIGGING, HIGH TEMPERATURE, AIR FLOW, BLADES, CAMERAS, COMPUTERIZED SIMULATION, COOLING, COOLING AND VENTILATING EQUIPMENT, DEMONSTRATIONS, EFFICIENCY, HIGH TEMPERATURE, INFRARED RADIATION, MEASUREMENT, MODELS, PYROMETERS, REGIONS, SURFACE TEMPERATURE, SURFACES, TEMPERATURE, TEST AND EVALUATION, TURBINES, VIDEO SIGNALS.
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE