Variable nozzle for a radial turbine

Abstract: The turbine nozzle (30) has a full complement of blades (18), for use, for example, in a compressed-air turbine. However, a pair of peripheral walls (32, 34), at opposite sides of a nozzle platform (12) block nozzle blade groups (38, 40). The walls prevent fluid flow through those blade groups and, consequently, the nozzle is given limited power. A method of achieving this includes machining away of as much of the walls (32, 34) as is necessary to enhance the power of the nozzle by exposing more of the nozzle blades to free fluid flow therethrough. By providing such walled, fully-bladed nozzles, and removing portions of the walls, one can meet any power requirement, from full power to any practical minimum, by removing the walls entirely, or removing only a minor portion of each, respectively.

Description: This invention relates to fluid turbines, and in particular to (a) turbine nozzles, and (b) a method of varying the power of such nozzles. Fluid turbines, for example, compressed air turbines, are designed to meet varying power requirements. A way of satisfying differing power requirements is to configure the nozzles thereof with differing numbers of blades. That is, for given circumstances, a nozzle can be formed with X number of blades for maximum power, X/2 for half power, and X/4 for one-quarter power. A nozzle ring, having at the inlet a throttle ring which is adjustable during operation, is known from DE-C-154 817. What has been long sought is a nozzle which is capable of meeting all possible power requirements. By this, the necessity to manufacture and stock a supply of variously bladed nozzles is ended. According to one aspect of the present invention, there is provided a turbine nozzle, having a platform having a periphery defining a substantially circular shape; a plurality of equally spaced blades having leading and trailing edges arrayed on said platform, adjacent to said periphery and defining a plurality of nozzle passages; and characterized by means formed about portions of the periphery of said platform, integral with the leading edges of sequential ones of said blades, for preventing a flow of fluid through said nozzle passages. According to a second aspect of the present invention, there is provided a method of increasing the power of a turbine nozzle, including the steps of providing a turbine nozzle which includes a platform having a periphery defining a substantially circular shape, a plurality of equally spaced blades having leading and trailing edges arrayed on the periphery of said platform and defining a plurality of nozzle passages adjacent to said periphery, and characterized by a peripheral wall integral with said leading edges of said blades, for preventing a flow of fluid through said nozzle passages; and by removing portions of said wall to permit fluid flow through sequential ones of said nozzle passages. For a better understanding of the invention and to show how the same may be carried into effect, reference will now be made, by way of example, to the accompanying drawings, in which:- Figure 1 is a perspective, exploded view of a portion of a compressed air turbine, and Figure 2 is a vertical illustration of the nozzle of Figure 1. As shown in Figure 1, an end plate 10 for a compressed air turbine comprises a platform 12 which has two sets 14 and 16 of blades 18 thereon. The blades 18 extend from the platform 12 in a normal attitude thereto. A rotor shaft seal 20 is received in the central recess 22 in the platform 12 and a bladed rotor 24 is set into the seal. An O-ring seal 26 sets against the end plate 10, and a spacer 28, for a complementary end plate (not shown), only a fragment thereof being shown, is interposed between end plate 10 and the complementary end plate. The platform 12, as can be seen in Figures 1 and 2, has a full complement of blades 18. Accordingly, the blades and platform, comprising a nozzle 30, is bladed for full power. However, a pair of walls 32 and 34 are coupled to the periphery of nozzle 30, in proximate adjacency to sets 38 and 40 of blades 18. The walls 32 and 34, describing arcs of equal length, inhibit a fluid flow through the sets of blades 38 and 40. The arc lengths of the walls 32 and 34 are formed by machining away portions of the as cast wall which completely circumscribes the platform 12. As shown, the walls 32 and 34, having heights from the platform 12 substantially the same as the heights of the blades 18 (as can be perceived in Figure 1), are each of approximately ninety degrees of arc. The nozzle 30, then, is capable of only about half its full power potential. According to the present method, machining away the walls in their entirety will provide a nozzle 30 capable of full power. Alternatively, by machining away half -- complementary halves -- of each of the walls 32 and 34 will render the nozzle capable of approximately three-quarters of its full power potential. According to this teaching, then, it is no longer necessary to design and construct nozzles with diverse bladings. Fully complemented-bladed nozzles can be formed with walls, like the walls 32 and 34, which circumscribe half, three-quarters, one-quarter, etc., as one chooses, of the blades 18. Then, by the expedient of machining away so much of the walls as will power the nozzle to the level required, a large number of power levels can be provided, even by going as far as removing the walls entirely.

Claims: A turbine nozzle (30), having a platform (12) having a periphery defining a substantially circular shape; a plurality of equally spaced blades (18) having leading and trailing edges arrayed on said platform, adjacent to said periphery and defining a plurality of nozzle passages; and characterized by means (32, 34) formed about portions of the periphery of said platform (12), integral with the leading edges of sequential ones of said blades, for preventing a flow of fluid through said nozzle passages. A turbine nozzle according to claim 1, wherein said fluid flow preventing means comprises a plurality of walls (32, 34). A turbine nozzle according to claim 2, wherein said walls (32, 34) form a pair on opposite sides of said platform (12). A turbine nozzle according to claim 1, 2 or 3, wherein fluid flow preventing means are integrally formed on said periphery. A turbine nozzle according to any one of the preceding claims, wherein said fluid flow preventing means circumscribes no less than approximately half of said blades (18). A turbine nozzle according to any one of the preceding claims, wherein said blades (18) extend normal to said platform (12) to a given height and said fluid flow preventing means (32, 34) also extend normal to said platform (12) to substantially the same height. A method of increasing the power of a turbine nozzle, including the steps of providing a turbine nozzle (30) which includes a platform (12) having a periphery defining a substantially circular shape, a plurality of equally spaced blades (18) having leading and trailing edges arrayed on the periphery of said platform and defining a plurality of nozzle passages adjacent to said periphery, and characterized by a peripheral wall (32, 34) integral with said leading edges of said blades, for preventing a flow of fluid through said nozzle passages; and by removing portions of said wall to permit fluid flow through sequential ones of said nozzle passages. A method according to claim 7, wherein said peripheral wall comprises two wall portions on diametrically opposite sides of said platform (12), respectively. A method according to claim 7, wherein said wall removing step is characterised by removing portions of said walls (32, 34) until fluid flow is permitted through the nozzle passages defined by approximately half of said plurality of blades (18).

Inventors: KIMBERLIN ROBERT R, KIMBERLIN, ROBERT R.
Applicants: INGERSOLL RAND CO, INGERSOLL-RAND COMPANY
Application year: 1990
Main classification: F01D9
IPC codes: F01D17, F01D9