US2015059A

US2015059A - Combustion turbine

Info

Publication number: US2015059A
Application number: US658872A
Authority: US
Inventors: Christiansen Johannes
Original assignee: Individual
Current assignee: Individual
Priority date: 1931-02-28
Filing date: 1933-02-27
Publication date: 1935-09-24
Anticipated expiration: 1952-09-24
Also published as: GB375739A

Description

Sept. 24, 1935. J. CHRISTIANSEN COMBUSTION TURBINE Filed Feb. 27, 1955 Y I Smaentor JoaW/yes C/rz'sanse/a Bg Y (Ittorneg Patented Sept. 24, 1935 UNITED STATES PATENT OFFICE COMBUSTION TURBINE Johannes Christiansen, Sorup-Schauby, Germany,

assignor of one-half to Alfred Oberle, Washington, D. C.,

Claims.

Ihis invention relates to turbines in general and in particular to turbines which are driven by combustion gases which may be produced by the combustion of liquid, gaseous or pulverized fuels.

It has already been proposed to construct a turbine rotor with a number of propeller blades having a concave driving surface and arranged so as to overlap each other on either side of the axis of rotation of the rotor. In this arrangement, the driving gases were made to impinge on the entire surface of the blade facing the inlet, but such an arrangement does not allow a very high turning moment to be obtained.

t is the object of the invention to obtain more power from the energy of the driving fluid by arranging propeller blades on a turbine rotor so that they are in the best position and of the best shape to allow the gases to act upon them in the most efficient manner.

According to the invention the driving faces of the propeller blades are made sinuous and they are so situated that the driving iluid impinges substantially only on concave portions of this surface. Several propeller blades may be provided and they are arranged so that the gases rst of all impinge upon a concave surface on one blade and are then deflected by a convex portion on t'o a concave surface on another blade.

When the turbine is to be driven by hot gases the inlet is preferably arranged to diverge towards the rotor so that the expansion which thus occurs cools them and prevents the blades and the rotor in general from being overheated.

In order that the invention may be thoroughly understood and be more readily carried into effect, an example of construction in accordance therewith will now be described with reference to the accompanying drawing which shows diagrammatically a cross-section through the working chamber of a turbine in accordance therewith.

The rotor consists of two discs b which are separated by two propeller blades a fixed to them and. are mounted on a shaft c in a casing g. The driving fluid is fed to the casing g through an inlet f and leaves the casing g through an outlet f.

The propeller blades a are roughly semi-circular, their outside surfaces being quite smooth. The inside surfaces of the blades a, however, which are the driving surfaces, are made sinuous and consist of two concave portions e and e' joined by a convex portion d. The blades a are xed to the discs b so as to be substantially tangential to the circumference of these blades at one end and to be considerably nearer the shaft c at the other end and are symmetrically disposed about the shaft c.

The driving uid which enters at f thus impinges upon the concave surface e of one blade a and, therefore, drives the rotor in a clockwise di- 5 rection. The convex portion d and the concave portion e of this blade a then deect the stream of fiuid towards the concave portion e on the other blade a, so that the rotor receives a further impulse in the clockwise direction while the gases l0 finally flow out through the outlet f.

In this way the driving uid impinges substantially only on the concave portions e which are farthest from the center of the rotor and the concave portions e which are near the center of the rotor merely help with the convex portions d to deflect the driving gases from one blade a to the other. Thus, the blades a are positioned and shaped so that the driving uid can do its work in the most efficient manner. It is further to be noted in this connection that the path of the fluid when leaving the second blade a is substantially parallel to the path of the gases impinging upon the rst blade 0:.

The construction which is described is particularly useful for turbines which are driven by combustion gases although it is suitable for turbines driven by any uid whatever. When hot combustion gases are used as the driving means it is inadvisable to use them while in a very hot condition because the rotor may thus become uncomfortably overheated. Toguard against this danger the inlet f is tapered and as seen in the drawing diverges towards the rotor so that by expansion the gases are cooled to a suitable temperature before they are used to drive the rotor.

Having now particularly described and ascertained the nature of our said invention and in what manner the same is to be performed, we declare that what we claim is:-

l. A turbine rotor provided with a casing and semicircular shaped blades forming a single channel for the passage of the driving fluid said blades being formed with sinuous surfaces and so situated that the driving iiuid impinges substantially only on concave portions of the sinuous surface of the propeller blades.

2. A turbine rotor according to claim l, wherein the surface of the propeller blades on which the driving fluid impinges is composed of two concave portions joined by a convex portion so that the driving duid is deected by the convex portion of one blade so as to impinge on a concave portion of another blade.

3. A turbine having a rotor according to claim l, wherein the surface of the propeller blades on which the driving uid impinges is composed of two concave portions joined by a convex portion so that the driving fluid is deflected by the conveX portion of one blade so as to impinge on a concave portion of another blade and provided with an inlet passagefor the driving Iluid which diverges towards the rotor.

4. A turbine rotor according to claim 1, wherein the casing housing the propeller blades has the shape of a bulbous funnel, an inlet comprising a narrow orice thru which the driving fluid enters the turbine and a discharge opening of larger area than the inlet thru which the driving fluid leaves the turbine.

5. A turbine driven by combustion gases having a rotor provided with two propeller blades forming, with a housing for the blades, a single one-Way passage for the gases, said blades having outside semicircular surfaces of uniform curvature and sinuous inside surfaces' and which are mounted so that the driving gases impinge substantially only on concave portions of the sinu- 10 ous faces of the propeller blades.

JOHANNES CHRISTIAN SEN.