The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a turbomachine including a non-destructive fastener element for joining components.
Gas turbomachines include a compressor portion linked to a turbine portion through a common compressor/turbine shaft and a combustor assembly. An inlet airflow is passed through an air intake toward the compressor portion. In the compressor portion, the inlet airflow is compressed through a number of sequential stages toward the combustor assembly. In the combustor assembly, the compressed airflow mixes with a fuel to form a combustible mixture. The combustible mixture is combusted in the combustor assembly to form hot gases. The hot gases are guided to the turbine portion through a transition piece. The hot gases expand through a number of turbine stages acting upon turbine buckets mounted on wheels to create work that is output, for example, to power a generator, a pump, or to provide power to a vehicle.
Each turbine stage may include a cover plate disposed about a central rotor that supports the buckets. The cover plates may reduce the effects of the hot gases on the central rotor and the buckets. Some cover plates may be shoe-horned into place about the central rotor. Other cover plates rely on in-field customization before mounting to the central rotor. Once installed, a fastener element, typically in the form of a pin, is passed through a base portion of each bucket to secure the cover plate to the rotor. The pin is often peened or staked in place to the base of the bucket. Removal of the pin may be both time and labor intensive resulting in undesirable down time for the turbomachine.
According to one aspect of an exemplary embodiment, a turbomachine includes a first component including a first surface and a second surface spaced from the first surface by a gap. One of the first and second surfaces includes a non-destructive fastener element receiving opening and a wire retention feature. A second component extends into the gap between the first and second surfaces. A non-destructive fastener element is detachably mounted to the first component. The non-destructive fastener element includes a post member and a wire member operatively connected to the post member. The post member extends into the non-destructive fastener element receiving opening preventing removal of the second component and the wire member engages with the wire retention feature to secure the non-destructive fastener element to the first component.
According to another aspect of the exemplary embodiment, a turbomachine includes a rotor including a radial outer edge having a blade mounting region provided with a plurality of blade mounts disposed circumferentially about the radial outer edge, a first groove defining member extending about the radial outer edge and a second groove defining member extending circumferentially about the rotor radially inwardly of the plurality of blade mounts. A plurality of blades is mounted to the rotor. Each of the plurality of blades includes a retaining component and a blade mounting portion. The retaining component includes a first surface and the blade mounting portion includes a second surface spaced from the first surface by a gap. One of the first and second surfaces includes a non-destructive fastener element receiving opening and a wire retention feature. A blade retaining element is received by the first and second groove defining members and extends into the gap between the first and second surfaces. A non-destructive fastener element is detachably mounted to the retaining component. The non-destructive fastener element includes a post member and a wire member operatively connected to the post member. The post member extends into the non-destructive fastener element receiving opening preventing removal of the blade retaining component and the wire member engages with the wire retention feature to secure the non-destructive fastener element to the retaining component.
These and other advantages and features will become more apparent from the following description taken in conjunction with the drawings.
The subject matter, which is regarded as the invention, is particularly pointed out and distinctly claimed in the claims at the conclusion of the specification. The foregoing and other features, and advantages of the invention are apparent from the following detailed description taken in conjunction with the accompanying drawings in which:
The detailed description explains embodiments of the invention, together with advantages and features, by way of example with reference to the drawings.
A turbomachine, in accordance with an exemplary embodiment, is indicated generally at 2 in
Turbine portion 6 includes a turbine rotor 30 that supports a plurality of buckets or blade components 33. Blade components 33, when exposed to the hot gases flowing through turbine portion 6, cause turbine rotor 30 to rotate. At this point, it should be understood that the number of turbine rotors may vary. As shown in
Each of the plurality of blade components 33 is coupled to turbine rotor 30 at corresponding ones of the plurality of blade mounts 43. Each blade component 33 includes an airfoil portion 59 that extends from a blade mounting portion 61. Blade mounting portion 61 is shown in the form of a dovetail member 63 that is received by dovetail slot 45. Each blade component 33 also includes at least one retaining component 66 having an outer surface 69 that is generally parallel to, and spaced from, an outer surface 72 of blade mounting portion 61. A second retaining component (not separately labeled) may also be provided. A gap 74 is formed between retaining component 66 and first outer surface 72 of blade mounting portion 61.
One or more blade retaining elements, 80 is mounted to radial outer edge 39 and held in place, at least in part, by retaining component 66. In accordance with an aspect of the exemplary embodiment, blade retaining element 80 takes the form of a plurality of segmented cover components, one of which is indicated at 81. Of course it should be understood that blade retaining element 80 may also take the form of a locking wire. Each segmented cover component 81 includes a hook element 83 that engages with second groove defining member 54 and a radial outer lip 85 that is extends into gap 74 and is received by first groove 50. Segmented cover components 80 may shield turbine rotor 30 from hot gases, may seal a coolant flow path, and may dampen vibrations, may axially retain blade components 33 or the like. Segmented cover component 81 is secured to turbine rotor 30 through a plurality of non-destructive fastener elements, one of which is indicated at 94 that extend through respective ones of retaining component 66 of each blade component 33.
In accordance with one aspect of the exemplary embodiment illustrated in
Reference will now follow to
Non-destructive fastener element 130 includes a post member 154 having a base portion 156 and a post portion 158. Base portion 156 includes a wire receiving passage 160 that extends generally perpendicularly to a longitudinal axis of post portion 158. Base portion 156 also includes an access port 166 that bisects wire receiving passage 160. A wire member 174 extends through wire receiving passage 160. Access port 166 provides access for a tool, such as a drill bit, to sever wire member 174 in the event that removal is not easily/readily accomplished, as detailed below. Wire member 174 extends from a first end 176 to a second end 177 through an intermediate portion 178. First end 176 includes a first hook section 180 and second end 177 includes a second hook section 181. First and second ends 176,177 are configured to be snap-fittingly received by first and second wire retaining features 140 and 142. First and second lead-in sections 144 and 145 facilitate insertion of first and second ends 176 and 177. Once installed, post portion 158 extends toward segmented cover component 81. Radial outer lip 85 prevents segmented cover component 81 from being withdrawn when non-destructive fastener element 130 is installed, as shown in
Reference will now follow to
Non-destructive fastener element 190 also includes a wire member 230 coupled to base portion 216. Wire member 230 extends from a first end 233 to a second end 234 through an intermediate portion 235. First end 233 extends through first wire receiving passage 221 and second end 234 extends through second wire receiving passage 223 such that a loop 239 is formed in intermediate section 235. With this arrangement, post portion 218 is passed through non-destructive fastener element receiving opening 204 and wire member 230 is flexed allowing loop 239 to pass over, and engage with, projection 198. Post portion 218 extends toward segmented cover component 81 to prevent removal.
At this point it should be understood that the exemplary embodiment describes a non-destructive fastener element for joining turbomachine components. While described as retaining a segmented cover component, it should be understood that the non-destructive fastener element may be used to join other structures both static and rotating. Further, it should be understood that in addition to being used in a turbine portion, the non-destructive fastener element may be used in the combustor assembly and or the compressor portion or other areas of the turbomachine. Further, it should be understood that the shape of the non-destructive fastener element may vary.
While the invention has been described in detail in connection with only a limited number of embodiments, it should be readily understood that the invention is not limited to such disclosed embodiments. Rather, the invention can be modified to incorporate any number of variations, alterations, substitutions or equivalent arrangements not heretofore described, but which are commensurate with the spirit and scope of the invention. Additionally, while various embodiments of the invention have been described, it is to be understood that aspects of the invention may include only some of the described embodiments. Accordingly, the invention is not to be seen as limited by the foregoing description, but is only limited by the scope of the appended claims.