Gas turbine generators

Abstract

A radial flow gas turbine generator (10) where the gas turbine generator (10) includes a shaft (30) having a rotor (20) of the generator (10), a compressor wheel (16) and a turbine wheel (18) fixed thereto. The shaft (30) is supported for rotation by a single bearing arrangement (38 provided at an axial position on the shaft (30) that is between the rotor (20) and the compressor wheel (16).

Claims

1. A radial flow gas turbine generator, the radial flow gas turbine generator including: a radial flow gas turbine section and an electrical generation section; a shaft having a rotor of the electrical generation section, with a compressor wheel and a turbine wheel of the gas turbine section fixed to the shaft; and a single bearing arrangement supporting the shaft for rotation, wherein said single bearing arrangement is at an axial position on the shaft between the rotor of the electrical generation section and the compressor and turbine wheel of the gas turbine section, wherein the rotor of the electrical generation section and the compressor of the gas turbine section are overhung on opposing sides of the single bearing arrangement.

2. The gas turbine generator as claimed in claim 1 wherein the single bearing arrangement includes two or more mechanical contact bearings.

3. The gas turbine generator as claim 2 wherein the mechanical contact bearings are rolling element bearings.

4. The gas turbine generator as claimed in claim 2 wherein the bearing arrangement includes bearings in a module that maintains a predetermined relationship between the bearings.

5. The gas turbine generator as claimed in claim 4 wherein the bearings are mounted within a sleeve.

6. The gas turbine generator as claimed in claim 5 wherein the bearings are mounted in a spaced apart relationship to one another within the sleeve.

7. The gas turbine generator as claimed in claim 6 wherein a resilient member is located between the bearings in the sleeve.

8. The gas turbine generator as claimed in claim 7 wherein the resilient member is a coil spring.

9. The gas turbine generator as claimed in claim 8 wherein the coil spring is located within the sleeve such that a first end of the coil spring abuts one of the bearings and an opposite end of the coil spring abuts a seat provided on the sleeve.

10. The gas turbine generator as claimed in claim 1 wherein the bearing arrangement is air cooled.

11. The gas turbine generator as claimed in claim 1 wherein the bearing arrangement is self-lubricating.

12. The gas turbine generator as claimed in claim 1, further comprising an oil wick system configured to lubricate the bearing arrangement.

13. The gas turbine generator as claimed in claim 1, further comprising a recirculating lubrication system configured to cool and lubricate the bearing arrangement.

14. A method of operating a radial flow gas turbine generator as claimed in claim 1, wherein the operating speed of the radial flow gas turbine generator is greater than the first resonant speed.

15. A vehicle comprising: battery cells; and a gas turbine generator in electrical communication with the battery cells, the gas turbine generator including a radial flow gas turbine section and an electrical generation section, a shaft, a compressor wheel and a turbine wheel of the gas turbine section, and a single bearing arrangement, the shaft having a rotor of the electrical generation section, the compressor wheel fixed to the shaft, the turbine wheel fixed to the shaft, and the single bearing arrangement supporting the shaft for rotation, the single bearing arrangement at an axial position on the shaft between the rotor of the electrical generation section and the compressor and turbine wheel of the gas turbine section, wherein rotation of the shaft produces electrical power to recharge the battery cells, wherein the rotor of the electrical generation section and the compressor wheel of the gas turbine section are overhung on opposing sides of the single bearing arrangement.

Description

BRIEF DESCRIPTION OF THE FIGURES

(1) FIG. 1 shows a longitudinal cross-sectional view of a gas turbine generator including a bearing arrangement according to the present invention;

(2) FIG. 2 shows an enlarged longitudinal cross-sectional view of the bearing arrangement of FIG. 1;

(3) FIG. 3 shows a side view of the rotating assembly of the gas turbine generator including the bearing arrangement, generator rotor, and gas turbine compressor and turbine;

(4) FIG. 4 shows a longitudinal cross-sectional view of the rotating assembly, bearing arrangement, generator rotor and gas turbine compressor and turbine of FIG. 3;

(5) FIG. 5 shows a longitudinal cross-sectional view of another rotating assembly, bearing arrangement, generator rotor and gas turbine compressor and turbine; and

(6) FIG. 6 shows an enlarged detail of the cross-sectional view of FIG. 5.

DETAILED DESCRIPTION

(7) Referring firstly to FIGS. 1 to 4 there is shown a gas turbine generator generally designated 10. The generator 10 includes a radial flow gas turbine section 12 and an electrical generation section 14. The gas turbine section 12 includes a compressor wheel 16 and a turbine wheel 18. The electrical generation section 14 includes a rotor 20 and a stator 22. The rotor and stator 20,22 are surrounded by a casing 23.

(8) The compressor and turbine wheels 16, 18 are provided with respective casings 24,26. The gas turbine section 12 is operable in a conventional manner which is known to those skilled in the art. Specifically, air drawn into the compressor wheel casing 24 through an annular inlet 28 thereof is compressed by the compressor wheel 16. Fuel is added to the compressed air and the fuel-air mixture is caused to combust. The expanding combustion gases pass to the turbine wheel casing 26 whereupon they impinge upon the turbine wheel 18 and cause rotation thereof. Energy may subsequently be recovered from the combustion gasses, for example via a heat exchanger. The recovered energy may be used to heat the air compressed by the compressor wheel prior to combustion.

(9) The electrical generation section 14 operates in a conventional manner which is known to those skilled in the art where rotation of the rotor 20 relative to the stator 22 generates electrical energy.

(10) The compressor and turbine wheels 16,18 and rotor 20 are coupled for rotation on a common shaft 30. In the embodiment shown, the shaft 30 comprises a turbine shaft section 30a and a generator shaft section 30b which are connected to one another. In the embodiment shown the connection is effected by a threaded projection 32 of the turbine shaft section 30a being received in a correspondingly threaded recess 34 of the generator shaft section 30b. It will be appreciated by the skilled addressee that other methods of joining the shaft sections 30a,30b may be employed. Alternatively, a single piece shaft may be utilised.

(11) The rotor 20 is further provided with an arrangement which, in use, supplies a flow of cooling air to the electrical generation section 14. In the embodiment shown, the arrangement is a radial cooling fan 36. It will be appreciated that other forms of arrangement may be utilised to move air in the manner described.

(12) Rotation of the cooling fan 36 causes air to be drawn into the casing 23 through apertures 25 of the casing as indicated by arrow 27. The air then passes around the stator 22, and between the stator 22 and rotor 20 as indicated by arrows 29. The air exits the casing 23 via an aperture 31 provided in the end thereof.

(13) In the embodiment illustrated in the figures the shaft 30 is supported for rotation in a bearing arrangement 38 provided in the electrical generation section casing 23. Also in the embodiment shown, the bearing arrangement 38 comprises a first annular bearing 40 hereinafter referred to as the generator side bearing 40, a second annular bearing 42 hereinafter referred to as the turbine side bearing 42, an annular spacer 44 positioned intermediate the bearings 40,42, and an axial spring 46 which extends between the bearings 40,42 and surrounds the annular spacer 44. In the embodiment shown, the bearings 40,42, spacer 44 and spring 46 are separate. In an alternative embodiment the bearings 40,42, spacer 44 and spring 46 may be incorporated into a module or cassette which can be fitted as a single item. Such an embodiment is described below with reference to FIGS. 5 and 6.

(14) Each of the bearings 40,42 is a rolling element bearing. Each bearing 40,42 includes an inner race, an outer race and a plurality of rolling elements disposed between the inner and outer races.

(15) It will be noted that bearing arrangement 38 is provided at an intermediate position on the shaft 30 such that turbine shaft section 30a extends from one side of the bearing arrangement 38, and the generator shaft section 30b extends from the opposite side of the bearing arrangement 38. It will further be noted that neither the turbine shaft section 30a nor the generator shaft section 30b are supported along their respective lengths by any other bearing arrangements. It will thus be understood that both the rotor 20 of the electrical generation section 14, and the compressor and turbine wheels 16, 18 of the gas turbine section 12 are overhung with respect to the bearing arrangement 38.

(16) By providing the bearing arrangement 38 at the aforementioned intermediate position of the shaft 30 enables the bearings 40,42 to be air cooled. As can readily be seen from the figures, the generator side bearing 40 is located adjacent the cooling fan 36 and is surrounded by the apertures 25 through which air is drawn by the cooling fan 36. The turbine side bearing 42 is located adjacent the compressor inlet 28. Both bearings 40,42 are thus provided at the respective “cool” ends of the gas turbine section 12 and electrical generation section 14.

(17) Optionally, additional cooling of the bearing arrangement 38 may be effected by utilising the air drawn into the compressor inlet 28 as indicated by arrow 48. The compressor wheel 16 is provided with a plurality of through apertures 50 which extend between the compressor inlet 28 and an annular space or passages 52 defined between the compressor wheel 16 and the shaft 30. Reduced pressure before the blades of the compressor causes some of the air entering the casing 23 to be drawn towards the compressor wheel apertures 50 as indicated by arrows 54.

(18) Air cooling of the bearing arrangement 38 permits the use of grease or oil wick lubrication for the bearings 40,42 and thus eliminates the need for a relatively complex lubrication system that feeds oil to the bearings 40,42. Air cooling of the bearing arrangement 38 further enables self-lubricating bearings 40,42 to be used as the temperatures experienced by the bearings 40,42, in use, do not exceed those at which the lubricating medium within the bearings 40,42 degrades.

(19) Referring now to FIGS. 5 and 6 there is shown longitudinal cross-sectional view of another rotating assembly, bearing arrangement, generator rotor and gas turbine compressor and turbine generally designated 100. Features common to the embodiment of the invention described with reference to FIGS. 1 to 4 are identified with like reference numerals prefixed with “1”.

(20) As before, the bearing arrangement 138 includes two bearings 140,142 which are maintained at a required axial separation with respect to one another by a spacer 144. In contrast to the bearing arrangement 38 of FIGS. 1 to 4, the bearings 140,142 are located within a tubular sleeve 156. The bore 158 of the sleeve 156 is provided with an annular seat 160 against which is located one end of a coil spring 146. The opposing end of the coil spring 146 abuts the bearing 140 which is proximal to the rotor 120. It will be appreciated that the mounting of the bearings 140,142 with a sleeve 156 enables the bearing arrangement 138 to be pre-assembled before being fitted to an appropriately sized bore of the casing 123.

(21) The sleeve 156 is further provided around its external periphery with a plurality of elastomeric rings 162. In the embodiment shown the sleeve 156 is provided four rings 162 which are provided in pairs at opposing ends of the sleeve 156. The function of these elastomeric rings 162 is twofold. Firstly, the rings 162 define a complaint mounting arrangement for the sleeve 156, and thus the shaft 130, within the casing 123. The pairs elastomeric rings 162 further serve to define an annular chamber 164 around the external periphery of the sleeve 156. The chamber 164 may be filled with a liquid such as oil through a port 166 in the casing 123 to damp movement of the sleeve 156 and shaft 130 in directions which are substantially perpendicular to the longitudinal centerline axis of the shaft 130.

(22) It will be understood by the skilled addressee that for a gas turbine generator 10 of the type described above to operate reliably, it must operate in such a way that harmful vibrations are not excited for any significant period of time. For such generators 10, the mass and stiffness characteristics may be arranged such that the generator 10 always operates at a speed lower than the first resonant vibration speed. Alternatively, such a generator 10 may be designed to operate at a speed above one or more resonant frequencies. Such a generator 10 would typically be accelerated through resonant speeds at a sufficient rate that no significantly harmful vibrations occur.

(23) While the embodiment described above relates to a gas turbine generator where the bearings are air cooled and grease lubricated, it will be appreciated that the double overhung configuration of the rotor, and compressor and turbine may be used in conjunction with other bearing arrangements. For example, the double overhung configuration may be used in conjunction with a conventional pressurised oil feed lubrication and cooling system. Alternatively, the double overhung configuration may be used in conjunction with a lubrication system where lubricant is supplied to the bearings from a reservoir by a wick.

(24) The gas turbine generator of the present invention may be used on an electric vehicle (EV) or hybrid electric vehicle (HEV) as a range extender apparatus. More specifically, the gas turbine generator may be operated to produce electrical power for the purpose of recharging battery cells of the EV or HEV.