Gas turbine cycle calculations: Thermodynamic data tables for air and combustion products for three systems of units

Thermodynamic data tabulations specifically designed for gas turbine cycle calculations are presented for 1 ° intervals from 200 K to 2200 K, and from 3500 R to 4000o R. The tables are similar to those of Fielding and Topps, but are rather simpler to use. They are presented in the following systems of units: (a) Engineering Units, K (b)...

Gas turbine cycle calculations thermodynamic data tables for air and combustion products

Thermodynamic data tabulations specifically designed for gas turbine cycle calculations are presented for 1º intervals from 200ºK to 2000ºK, and from 350ºR to 3600°R. The tables are similar to those of Fielding and Topps, but are rather simplier to use, and are available in ºR as well as ºK. Numerical examples illustrating their use are included...

Gas turbine cycle calculations: differential methods in the analysis of equilibrium operation

The equilibrium operalton of a simple turbojet engine is analyzed, using logarithmic differential methods to infer performance changes about a design point. A simple method assuming constant specific heats and ignoring mass addition effects, is compared with a more rigorous analysis where both these effects are considered; it is shown that the...

Structural analysis of turbine rings: calculated stresses in scalloped rings of variable section

Complementing an earlier study on constant-sectien turbine rings, stress data are presented for variable- section turbine ring segments Buitable for carrying tbe turbine rotor blades in a tip-driven turbofan. These pinned-end segments have a constant outer radius and a variabie radial depth in order to achieve a desirable flexibility. Very...

Turbine drives for VTOL turbofans: further investigations with a tip turbine drive

A tip turbine drive suitable for VTOL lifting fans is described and test results are presented. The measured total head efficiency of the turbine was about 82 percent. A substantial proportion of the turbine losses was attributed to the unconventional stator vanes. A stepped labyrinth seal provided a reduction in hot gas leakage from the turbine...

Gas turbine cycle calculations design-point performance of turbojet and turbofan engines

An accurate and comprehensive method for calculating the design-point performance of turbojet and turbofan engines is described in this report . Analyses of the component processes that comprise a cycle are developed in detail from fundamental thermodynamic relations ta the actual equations programmed for the computer. The structure and cading...

Turbine drives for VTOL turbofans: preliminary results with an experimental tip turbine drive

A 36 -in . diameter tip turbine driven VTOL fan incorporating a free-floating turbine blade carrier is described. The blade carrier remained eccentric over the speed range covered and limited the maximum rotational speed to 79 percent of that desired. Turbine and fan performances are presented and the results of a comparison between the latter...

Gas turbine cycle calculations: generation of thermodynamic data for dry air and combustion products

A method is presented for generating thermodynamic data (specific heat, enthalpy, and entropy) as functions of temperature and fuel/air ratio, for ranges appropriate to gas turbine cycle calculations. Comparisons of the generally used tabulations of thermodynamic data are made, and specific algebraic expressions are developed which yield results...

Structural analysis of turbine rings: Calculated stresses in scalloped rings of constant section

Calculated stress data are presented for turbine rings suitable for tip-driven turborotors; these rings, whose function is to carry the turbine rotor blades, consist of short independent segments which are pinned to the supporting fan blades, and are arched or scalloped ta carry the operating leads more effectively. It is demonstrated that the...

Turbojet thrust augmentation: Flight test results for a reheat system employing fuel injection upstream of a two-stage turbine

Flight experiments on a reheat system, in which part of the reheat fuel was injected upstream of a two-stage turbine, are described. The system was fitted to an Orenda 14 engine installed in a Sabre 6 aircraft. The reheat system was stable over the range of conditions explored, and operated satisfactorily at the ceiling of the aircraft with a...

Turbojet thrust augmentation: Flight measurements of the turbine blade cooling accompanying the pre-turbine injection of reheat fuel with an Orenda 14 engine in a Sabre 6 aircraft

Turbine blade temperature data, obtained with a thermocouple-slipring instrumentation system, are presented for an Orenda 14 engine, which was flight tested both with and without reheat at altitudes ranging from 20,000 to 50,000 feet. The blade temperatures in the unreheated engine were found to be determined primarily by the variation in the...

Powerplants for VTOL aircraft: A proposed dual-operation system using wing-immersed fans for vertical thrust

Calculated performance and weight data are presented for a category of VTOL powerplants in which highly loaded fans (500 lb./ft²), immersed in the wings, are used to augment the hovering thrust of conventional turbojet engines. The augmentation ratio, shown to be of the order of 3.5, implies a satisfactory matching of the cruising and hovering...

Powerplants for VTOL aircraft: performance calculations for several hypothetical turbofan engines

Calculated performance data are presented in tabular form tor a wide range of altitudes, forward speeds, and engine speeds, for four hypothetical aft-turbofan engines, of bypass ratios 0, 1.39, 3.13, and 8.24. These performance data are used along with weight estimates to illustrate the application of turbofan engines to a typioal VTOL mission....

Laboratory and flight technique for the measurement of the temperature of turbine blading

The evolution of a flight-worthy instrumentation system for measuring turbine rotor blade temperatures in an Orenda 14 turbojet engine is described. The system comprises sheathed chromel-alumel thermocouples installed in drilled turbine blades and used in conjunction with mercury sliprings mounted in the exhaust bullet of the engine. The...