Patent GB-711985-A (GB)
Title: Improvements in gas turbines
IPC: F02C7/16
Filed: 1952-01-16
Abstract: 711,985. Jet propulsion plant: gas turbine plant; elastic-fluid turbines. ZBOROWSKI, H. P. G. A. R. VON. Jan. 16, 1952 [Jan. 18, 1951], No. 1222/52. Class 110(3) [Also in Group XII] In a gas turbine plant comprising a rotor wheel having hollow, metal blades each provided with radial partition means extending from the blade root to a point short of the blade tip so as to define at least two radially extending elongated chambers communicating with one another close to the blade tips and wherein one of the said chambers is limited by the blade wall in contact with the gaseous stream whilst the other is screened therefrom by the first mentioned chamber, the chambers are so arranged and dimensioned that a heat conveying stream of liquid, which is conveyed along a closed path including said blades, flows in a liquid state both centrifugally through the second chamber and centripetally through the first chamber and the said closed path, which passes through heat extracting means, extends through both rotating and fixed elements of the turbine plant. The turbine rotor comprises inner and outer ports T<SP>2</SP>, T<SP>1</SP> made of steel and an aluminium alloy respectively. The turbine blades A are made from an aluminium alloy and are formed integral with or are secured to either the outer or the inner ports T<SP>1</SP>, T<SP>2</SP> as shown in Figs. 1 and 5 respectively. Cooling liquid is fed through pipes 2 and radial passages q in the turbine blades to the jacket of the combustion chamber C from whence it is returned to a tank 10 after being cooled in a heat exchanger 4. The rotary movement of the coolant within the parts T<SP>1</SP>, T<SP>2</SP> is respectively increased and braked by fins 5 or the walls of the passage q are disposed close together so that the friction will brake the flow of coolant therethrough. The coolant may be water, mixture of water and methanol or a fuel, such as oil or kerosene. for the engine. When fuel is used as a coolant it may lubricate the bearing 14 and supply the injectors 13 through, a tapping as shown. The coolant may be circulated in series through the turbine and either the first stages of the compressor rotor or the propeller of a turbo-prop. A multi-stage turbine rotor, Fig. 6, comprises an outer casing T having the blades integral therewith and members Ta, Tb as shown for locating the pipes 2a within the blades. A ducted fan turbine engine, Fig. 7, comprises compressors 20a. 20b driven by a turbine M<SP>1</SP> together with a contra rotating airscrew H<SP>1</SP> - - - H4 driven by a turbine M<SP>2</SP> and a windmill K for feeding fuel to the outer duct and igniting it therein. The ducted fan turbine engine is cooled by fuel which is fed from a tank R to a point a and thence to the turbines and the windmill, the latter being supplied with fuel through a valve U. The fuel is fed in series through the rotor blades of the turbines M<SP>2</SP>, M<SP>1</SP> and is then fed in series through the stator blades V<SP>2</SP>, V<SP>1</SP> of the turbines to the jacket of the combustion chamber. Part of the fuel is now fed to the injectors 13 and the remainder is recirculated to the tank R through the blades of the airscrew H<SP>1</SP> which is partitioned as shown. The exhaust gases from the turbine M<SP>2</SP> are discharged into the outer duct through the hollow airscrew H<SP>2</SP>.