CENTRIFUGAL GAS TURBINE

Abstract: Contrarotating outward-flow gas turbine without stators and with two rotors (1 and 2) which set in motion the power shaft (3) and the compressor shaft (17), respectively. The inlet air (19) is sent through the impellers (20) of the outward-flow compressor to the manifold (22) and from there to the regenerator (24) where it is preheated; then, it reaches the combustion chamber (14) and from there it expands to the rotors, and finally passes through the exhaust manifold (27). The rotors (1 and 2) contrarotate coaxially on their bearings (11), both rotors having one or a plurality of rings of vanes (5, 6, 7, 8), and additionally flow guiding fins (9).

Description: This invention refers to a turbomotor as described in the preambles of claims 1 and 2. Such a turbomotor is disclosed in FR-A-740285, which differs as follows: The rotors form its inner combustion chamber. The vanes are arranged in eight rings around the inside combustion chamber. One burner feeds this combustion chamber directly. Both rotors are applied to the power shaft. This device has neither the compression phase of the turbines Brayton cycle, nor regenerator. Gas axial turbines of medium and high output are predominant, while those of low output are seldom used, due to the following limitations: Proportionatelly significant losses of pressure. Reduced efficiency of the small vanes. High rotors regime. The engine ends up being excessively bulky. The invention attempts to resolve the problems faced by small axial turbines: Reduced pressure losses of the turbine. More efficient vanes due to their shape, size and lower number. A lighter engine. A turbomotor wich meets these requirements is described in claims 1 and 2. Description of the drawings. Fig.n° 1. It is a longitudinal section of the motor, with the double disk exterior of the turbine. Fig.n° 2. It is a section of the turbine, with the two rotors, both of them with one disk and ring of vanes. Fig.n° 3. It is a cross section, in which the vanes of each rotor and guiding fins can be seen. This motor is principally for means of transport. The description explains the turbomotor invention and more especifically its turbine. The turbine consists of an interior reaction rotor (2) , counterrotating within another exterior reaction rotor formed of the two disks, to drive the compressor (4) and power shaft (3) respectively by means of concentric shafts mounted on bearings, in the fourth motor compartment. The combustor (14) is directly coupled over the central inlet (10) of the turbine to supply the centrifugal gas flow that straight fins of the interior rotor distribute the gas radially towards the vanes. These outward-flow vanes (5 and 6) form nozzles of opposing curvature in each rotor (fig. 3,n°15) The interior rotor is used to drive freely the compressor, while the exterior rotor drives the power shaft of the motor by means of the reducing gear (28). The annular regenerator (24) is located in the periphery of the exterior rotor vanes in order to take up the exhausted gases which preheat the compressed air which circulates in the interior of the regenerator. The distinctive characteristic features of the turbine are its exterior rotor of two disks (1-1) between which the ring of vanes (5) is arranged and its moving feed inlet (10) formed of the exterior disk of this rotor and also the annular regenerator. The turbomotor can also be constructed with the turbine which distintive characteristic being its interior (2) and exterior (1) reaction rotors of only one disk and one ring of outward-flow vanes, counterrotating one within the other and mounted on bearings on their respective coaxial shafts. This turbine's other distinctive characteristic is the feed inlet which is fixed to the crankcase, with the radial gas distribution fins fixed to the interior rotor or the crankcase. Furthermore this turbine feed system allows the flow rate required by each size of turbine The turbine is mounted in the crankcase with the regenerator (24) and the other variable conventional components to make up the engine. The starter motor (16) is located in the front part of the engine, connected to the compressor shaft (17) by means of the reducing gears (18). The radial compressor (4) has a diffuser (21) of diverging channels and an air manifold (22) located in the first compartment of the engine crankcase (23). The turbine is housed in the fourth motor compartment (12), the exhaust manifold of which located the annular regenerator (24). It is situated in the periphery of the exterior rotor vanes to collect the exhaust gases and it is connected at one end to the compressed air manifold (22) and at the other to the combustor (14). The reducing gear (28) which transmits the mechanical energy of the rotor to the power shaft (3), is located in the second (25) and third (26) motor compartment. The combustor (14) is a reversible type combustor and is located outside the motor directly connected to the turbine inlet (10). The interior rotor (2) is connected by its shaft directly to the compressor so that it can operate freely. The exterior rotor is connected by the reducing gear to the power shaft. The engine casing is characterized by its simplicity and compactness. This is due to a number of factors, the location of the regenerator in the exhaust manifold, the exterior combustor, the rotation of the rotors one within the other and the short lengh of the shafts, all of which reduce the volume and weight of the motor.

Claims: A turbomotor comprising: a crankcase; a stator free counterrotating outward-flow gas turbine consisting of an exterior reaction rotor (1) and an interior counterrotating reaction rotor (2) arranged within the exterior rotor (1),said rotors (1, 2) having concentrically arranged shafts mounted on bearings (11) within said crankcase and said exterior rotor (1) being connected to a power shaft (3); a ring of interior vanes (6) arranged on said interior rotor (2) and a ring of exterior vanes (5) arranged on said exterior rotor (1), said interior vanes (6) and said exterior vanes (5) having an opposing curvature; and a combustor (14) connected to a central inlet (10) of said turbine; characterised in that said interior rotor (2) is connected to a compressor (4); a regenerator (24) is located in said crankcase in the periphery of the ring of exterior vanes (5); said exterior rotor (1) is formed of two disks between which the ring of interior vanes (6) is arranged, an extension of one of said disks forming said central inlet (10); and guiding fins (9) are arranged on said interior rotor (2) to distribute the gas entering said turbine radially towards the vanes. A turbomotor comprising: a crankcase; a stator free counterrotating outward-flow gas turbine consisting of an exterior reaction rotor (1) and an interior counterrotating reaction rotor (2) arranged within the exterior rotor (1),said rotors (1, 2) having concentrically arranged shafts mounted on bearings (11) within said crankcase and said exterior rotor (1) being connected to a power shaft (3); a ring of interior vanes (6) arranged on said interior rotor (2) and a ring of exterior vanes (5) arranged on said exterior rotor (1), said interior vanes (6) and said exterior vanes (5) having an opposing curvature; and a combustor (14) connected to a central inlet (10) of said turbine; characterised in that said interior rotor (2) is connected to a compressor (4); a regenerator (24) is located in said crankcase in the periphery of the ring of exterior vanes (5); each of said exterior rotor (1) and said interior rotor (2) is formed of a single disk on which the ring of vanes (6) is arranged; said central inlet (10) is fixed to said crankcase; and guiding fins (9) are arranged on said interior rotor (2) or on said crankcase to distribute the gas entering said turbine radially towards the vanes.

Inventors: ABUNDANCIA DE SANTIAGO RAMON, ABUNDANCIA DE SANTIAGO, RAMON
Applicants: ABUNDANCIA DE SANTIAGO RAMON, ABUNDANCIA NAVARRO CRISTINA, ABUNDANCIA NAVARRO JUAN CARLOS, ABUNDANCIA DE SANTIAGO, RAMON, ABUNDANCIA NAVARRO, CRISTINA, ABUNDANCIA NAVARRO, JUAN CARLOS
Application year: 1996
Main classification: F01D1
IPC codes: F01D1, F02C3, F01D5