US 4,241,576 A · Gas turbine engine

Abstract

The gas turbine engine includes a centrifugal fan having radial blades for receiving inlet air through inner entrance openings to spaces between adjacent blades. The air passes through outer exit openings from the spaces between the blades. Stationary inner and outer circumferential segments define closure members which successively eclipse the inner entrance and outer exit openings of the centrifugal fan blades when the fan rotates to position adjacent blades between the closure members. The closure members and space between the blades thus define closed combustion chambers. Fuel is injected and ignited so that continuous combustion takes place at constant volume, the exhaust gases escaping through the outer exit openings when rotation of the fan positions these openings beyond the outer closure members. This continuous combustion at constant volume provides for increased efficiency in the gas turbine engine over the Brayton cycle constant pressure type turbine engine.

Claims8

Dependent claims

A gas turbine engine including a centrifugal fan having radial blades and receiving inlet air through the inner entrance openings to spaces between adjacent blades, said air passing through outer exit openings from said spaces;

inner and outer circumferential segments defining closure members for successively eclipsing said inner entrance and outer exit openings when relative rotation between said fan and segments positions said spaces between said closure members to thereby define closed combustion chambers;
and means for injecting and igniting fuel into said closed combustion chambers so that constant volume continuous combustion takes place to provide increased efficiency over a Brayton cycle constant pressure type turbine engine.

A gas turbine engine including, in combination:

(a) an outer cylindrical housing having front and rear air inlet and exhaust gas outlet axially aligned openings;
(b) an elongated axial shaft mounted in said body for rotation, said shaft carrying a front, central and rear spindle;
(c) compressor means mounted on said front spindle for rotation therewith;
(d) a centrifugal fan having radial blades mounted on said central spindle for rotation therewith;
(e) a turbine means mounted on said rear spindle for rotation therewith;
(f) stationary segmented inner and outer closure members defining semi-cylindrical cavities successively juxtaposed to inner and outer entrance and exit portions of said blades such that the inner entrance and outer exit openings to spaces between adjacent blades are successively simultaneously closed off by said members as said fan rotates to define constant volume combustion chambers;
(g) fuel injection means positioned to inject fuel in the spaces between adjacent blades just prior to being closed off by said inner and outer closure members;
and
(h) ignition means for igniting the fuel-air mixture in said constant volume combustion chamber so that combustion takes place continuously under constant volume, exhaust gases passing from the outer exit openings of the spaces between adjacent blades after passing the outer closure members to drive said turbine and maintain rotation of said spindle shaft, said compressor passing air into the inner portion of said centrifugal fan to be received in said inner entrance openings.

6 more elements

Dependencies are inferred from the claim text.

Gas turbine engine

Life of this patent

Gas turbine engine

Life of this patent

Abstract

Claims8