// I apologize forcomputer translation. Unfortunately Iam unable toperforma professional translation //
Turbojet enginesthat useRanque-HilschEffect
Today, all existing types of jet engines, has very serious contradiction which difficult to solve by conventional methods.
On the one hand, if the temperature of outgoing gases after combustion chambers is higher, the efficiency and economy of the entire device is higher.
On the other hand, the rise of temperature of the gases up to 1500*C requires the use of expensive materials and technologies for the manufacture of gas turbine blades.
As an example - the usage of the single crystal alloys or alloys which are alloyed by means of usage rare and expensive additives.
It can use the cooled blades, but they are difficult for manufacturing and its design ill-suited for use in the low power and compact engines.
Designing of the engines for cruise missiles, small aircrafts and "drones" has especially serious problem.
Ideally, designers would like to have an engine where the temperature of the main gas flow would have exceeded 2000 *C, but temperature of gases that entering to the turbine which drives the air compressor, would be below 900 *C, without addition of the cold air.
How this can be achieved?
There is a simple device that works on the Ranque-Hilsch Effect, which is intended for the stratification of the initial gas stream into two gas streams of different temperatures.
This device requires usage of heat-resistant materials for conical tube of stratificater and reflecting element only.
The simplest turbojet for cruise missiles and "drones"
What is important, in this design, to produce acceptable traction characteristics can be by usage of cheaper fuel with high specific gravity instead of expensive jet fuel.
Such replacement is very important for small aircrafts and the "drones" because it allows to sharply increase their range.
In a conventional turbojet engines, the turbine of air compressor receives about 25% of the total number of generated gases.
When the stratification into two streams is used, if standard kerosene with temperature of combustion 1900 - 2000 *C is used as a fuel - the temperature of "hot" flow will be approximately 2500 *C and the temperature of "cold" flow will be approximately 850-900 *C;
As you can see almost it is ideal operating temperature.
When a diesel fuel with temperature of combustion of the 1500 - 1700 *C is used - the temperature of "hot" flow will be about 2000 *C and the temperature of "cold" flow will be about 750-800 *C.
As you can see it is quite acceptable.
When jet engine that uses the vortex flow stratification is located within the tube that is open on both sides, there is a strong injection effect that gives the possibility of using this type of jet engine as the base of a Ram Turbofan Engine
Such a cheap, disposable engine, capable of a maximum thrust at speeds ranging from 350-450km / h and up to 950km / h - almost perfect for cruise missiles.
The scheme of a ramjet-Turbofan Engine based on the above-described
Using this scheme, designed by modules, it can create a whole range of jet engines for small aircraft or drones.
Turbofan Engine of classical scheme, with combustion chambers using vortex effect
Exhibit 1
Explanatory figure for the double-disk turbine with horizontal blades (turbine wheels - a counter-rotation)
