Compressor or turbine

Abstract: A centripetal compressor (1) comprises a compressor housing (3), a compressor wheel (4) mounted within the housing (3) and having compressor blades (5). The compressor housing (3) comprises a cover plate (6) and a diffuser flange (9) that is fixed to both the cover plate (6) and to a bearing housing (13). The diffuser member (2) has an outer peripheral portion attached to the cover plate and a radially inner portion attached to the bearing housing (13). A frangible groove (22) defined in the diffuser flange (9) at a position intermediate the outer peripheral and the radially inner portions so as to enable predictable fracture of the diffuser flange (9) during failure of the compressor wheel (4).

Description: The present invention relates to improvements in or relating to centripetal compressors and turbines particularly, but not exclusively, compressors and turbines used in turbo-chargers as applied to internal combustion engines. Turbo-chargers are generally designed to increase the inlet pressure of an internal combustion engine thereby increasing its power and efficiency. In a conventional design a centripetal compressor is driven by a centripetal turbine that is powered by the exhaust gases of the internal combustion engine. Such turbo-chargers are for example known from GB-A-2 277 129. A centripetal compressor of a turbo-charger generally comprises a compressor housing which receives a rotary compressor impeller with radially extending blades. The compressor housing comprises a cover plate, a portion of which closely follows the contours of the impeller blades and a portion of which defines an annular inlet passageway, and a diffuser flange that is fixedly connected between the cover plate and a bearing housing that retains the bearings for the compressor and the turbine. The diffuser may be fixed to the bearing housing by means of set screws or alternatively may be cast integrally with the bearing housing. There is an ever-increasing demand for turbo-chargers of higher performance particularly with vehicles of high horse power. In order to meet this demand it has been necessary to manufacture the compressor impeller from titanium so that the compressor can withstand the high pressure ratios and arduous operating conditions. A disadvantage of an impeller made from titanium or another high density material (e.g. stainless steel) relative to the current aluminium alloy impellers is that the increased density makes the impeller more difficult to contain in the event of its failure. Failure of the compressor impeller can occur through defects in the titanium, consistent use of the turbo-charger at speeds in excess of the top speed limit, or fatigue damage to the material caused by continually cycling between high and low turbo-charger speeds in extreme duty cycles. When the compressor impeller fails in use it is desirable to contain the radially projected fragments within the compressor housing to reduce the potential for damage to the turbo-charger or injury to personnel. Generally small fragments are relatively easily contained but larger fragments tend to damage the compressor housing or diffuser flange through their force of impact. At particular risk is the connection between the diffuser flange and the bearing housing. If the two are separated oil leakage from the bearing housing can occur thereby increasing the risk of fire in the engine compartment or failure of the engine. It is known, for experimental purposes only or for containment verification tests, to cut a slot in a rear face of the compressor impeller to ensure that when failure occurs it splits into two parts of predictable size and mass. The compressor housing and diffuser flange can then be designed accordingly to ensure containment of the fragmented impeller. However it has still been known for the fragments to prise the compressor housing from the diffuser flange successfully. Attempts to rectify this have included the adoption of a compressor cover manufactured from spheroidal graphite iron. However, this has not proved satisfactory as the material does not absorb as much energy as desired and therefore impact loads transferred to the diffuser flange and bearing housing are greater than normal. Another known approach is to strengthen the diffuser flange in order to improve the chances of containment of the fragments but this has resulted in the impact load of the fragments being transmitted to the set screws connecting the bearing housing and the diffuser flange and caused them to shear or be otherwise torn from the bearing housing. Modifications to the design of the connection between the bearing housing and the diffuser flange to reduce the risk of it being damaged would involve significant changes to the structure of the connection design and therefore significant cost. It is an object of the present invention to obviate or mitigate the aforesaid disadvantages. According to the present invention there is provided a centripetal compressor comprising the features of claim 1. In a preferred embodiment of the present invention the weakened region is in the form of a frangible groove which is preferably annular. The compressor wheel may be manufactured from titanium to withstand high pressure ratios or high temperatures. According to a further aspect of the present invention there is provided a turbo-charger with turbine driving a centripetal compressor as described above. A specific embodiment of the present invention will now be described, by way of example only, with reference to the accompanying drawings in which: Figure 1 shows an axial cross-section of a turbo-charger incorporating a compressor in accordance with the present invention; Figure 2 shows a front view of a diffuser flange of the present invention; Figure 3 shows a cross-section view, along line A-A, of the diffuser flange of figure 2; and Figure 4 shows an axial cross-section of an alternative embodiment of the turbo-charger. Referring now to the drawings, figure 1 shows a turbo-charger incorporating a centripetal compressor (according to the present invention) illustrated generally by reference numeral 1 and a centripetal turbine illustrated generally by reference numeral 2. The compressor 1 comprises a housing 3 which houses a rotary compressor impeller 4 with radially extending impeller blades 5. The compressor housing 3 comprises an annular cover plate 6 that is configured so as to define an annular inlet 7 disposed around a front portion of the compressor impeller 4 and an annular outlet passageway 8 disposed adjacent the radial tips of the impeller blades 5, and a diffuser flange 9 that is disposed at the rear of the compressor impeller 4. The turbine 2 similarly comprises a turbine impeller 10 received rotatably in a turbine housing 11 and mounted on the end of a rotary shaft 12 that is common to the compressor impeller 4. The turbine 2 is of conventional design and is not described in detail here. Intermediate the compressor and turbine housings 3,11 there is a bearing housing 13 with a central aperture 14 that receives the rotary shaft 12, the ends of which project into the compressor and turbine housings 3,11 and support the compressor and turbine impellers 4,10. The bearing housing 13 contains bearings 15 that support the shaft 12 and which are lubricated via conduits indicated at 16. The diffuser flange 9, shown in detail in figures 2 and 3, is of general disc-like configuration with a central aperture 17 for receiving the rotary shaft 12. The periphery of the diffuser flange 9 has a shallow rim 18 by which the diffuser 9 is connected to the cover plate 6 whereas a central portion 19 of the flange 9 is relatively thick and has four equi-angularly spaced apertures 20 by which the diffuser flange 9 is fixed to the bearing housing 12 by set-screws 21 (one only shown in figure 1). Immediately outboard of the set screw apertures 20 there is a machined annular groove 22 (not shown in figure 1) that significantly reduces the thickness of the diffuser flange 9 in that area. The annular groove 22 provides a region of weakness in the diffuser flange 9 and allows the region of failure of the diffuser 9 to be predicted. Should the compressor impeller 4 fail in use the fragments are projected radially outwards to the cover plate 6. The force of impact of the fragments puts strain on the cover plate 6, the diffuser flange 9 and the connection therebetween at the rim 18 and the first point of failure will be at the weakened groove 22 in the diffuser flange 9. This ensures that the connection between the bearing housing 13 and the diffuser flange 9 is maintained intact thereby avoiding the possibility of oil leakage. A significant portion of the diffuser flange 9 remains attached to the cover plate 6 and thereby provides, in combination with the cover plate 6, a robust container for the retention of the impeller fragments. In an alternative embodiment shown in Figure 4 the diffuser flange 9 is shown as being integral with the bearing housing 12. It will be appreciated that the invention is also applicable to the turbine stage of the turbo-chargers in order to prevent the bearing housing leaking oil into the exhaust and creating the risk of both fire and explosion. A groove or other weakness may be provided by machining into a flange indicated by reference numeral 23 in figure 1. The diffuser flange may be weakened locally in any suitable way; the annular groove described above is to be regarded as an example only. Moreover, the impeller could be constructed from any suitable material having a higher density than aluminium.

Claims: A centripetal compressor comprising a compressor housing (3), a compressor wheel (4) mounted within the housing (3) and having compressor blades (5), and a bearing housing (13), the compressor housing (3) comprising a cover member (6) and a diffuser member (9) that is fixed to both the cover member (6) and the bearing housing (13), the diffuser member (9) having an outer peripheral portion (18) attached to the cover member (6) and a radially inner portion (19) attached to the bearing housing (13), characterised in that the diffuser member (9) has a weakened region (22) defined at a position intermediate the outer peripheral and the radially inner portions (18,19) at which stress will be concentrated under extreme impact loads such that in the event of compressor failure the diffuser member (9) will preferentially fracture at said weakened region (22). A centripetal compressor according to claim 1, wherein the weakened region is in the form of a groove (22). A centripetal compressor according to claim 2, wherein the groove (22) is annular. A centripetal compressor according to claim 1, 2 or 3, wherein the compressor wheel (4) is manufactured from titanium. A turbo-charger with turbine driving a centripetal compressor according to any one of the preceding claims. A centripetal turbine comprising a turbine housing (11), a turbine wheel (10) mounted within the housing (11) and having turbine blades, and a bearing housing (13), the turbine housing (11) comprising a cover member and a flange member (23) that is fixed to both the cover member and the bearing housing (13), the flange member (23) having an outer peripheral portion attached to the cover member and a radially inner portion attached to the bearing housing (13), characterised in that the flange member (23) has a weakened region defined at a position intermediate the outer peripheral and the radially inner portions at which stress will be concentrated under extreme impact loads such that in the event of turbine failure the flange member (23) will preferentially fracture at said weakened region (22). A turbo-charger with a turbine according to claim 6 driving a centripetal compressor.

Inventors: FULLER JOHN, FULLER, JOHN
Applicants: HOLSET ENGINEERING CO, HOLSET ENGINEERING COMPANY LIMITED
Application year: 1998
Main classification: F04D25
IPC codes: F01D21, F04D29, F04D25