BACKGROUND OF THE INVENTION
This invention relates generally to gas turbine engines, and more specifically to turbine frame hanger lock assemblies and methods of assembling the same.
At least some known gas turbine engines include a frame that supports a rotor assembly. For example, gas turbine engines may include one or more rotor shafts supported by bearings which, in turn, may be supported by generally annular engine frames. An engine frame may include a generally annular casing spaced radially outwardly from an annular hub, with a plurality of circumferentially spaced apart struts extending therebetween. In some frame applications it may be necessary to protect the struts with fairings that have higher temperature capability. Because temperature variances can cause metals to expand and contract, it is desirable to separate high temperature engine components such as the flow path components, from comparatively low temperature peripheral components such as the frame components. To attach flow path components to the frame components, one or more hangers are used. The hangers serve to attenuate heat transfer from flow path components to frame components. Primarily, these hangers serve to affix flow path components in predetermined positions relative to frame components.
In some implementations, hangers are annular components with a curved cross-section. The outermost surface of the hangers contain apertures and are fastened (e.g., with bolts threaded through the apertures) to the frame of the turbine engine. The innermost surface of the hangers can be fastened to the flow path components, also utilizing apertures for receiving fasteners (e.g., bolts). In some cases, a single hanger may be used to attach a single flow path component to a frame component. In other cases, a single hanger may be used to attach multiple flow path components to a frame component. Each hanger conventionally requires a number of fasteners, adding a significant time burden to installation. Furthermore, the number of hangers and corresponding large quantity of fasteners contribute to the overall weight of the turbine engine. Even further, the use of bolts to attach hangers to various flow path and frame components inherently requires penetration of both the hangers and the respective components, increasing the potential for stress related failures in the gas turbine engine.
BRIEF DESCRIPTION OF THE INVENTION
In one aspect, a system for use in limiting axial movement between a hanger and a fairing assembly within a turbine assembly is provided. The hanger includes an inner radial hanger bend portion that defines a hook channel therein. The fairing assembly includes an outer surface, a hook member extending from the outer surface to mate with the hook channel, and a circumferential groove defined in the outer surface such that at least a portion of the hanger bend portion is positioned between the circumferential groove and the hook member. The system includes a retention member sized for insertion into the circumferential groove, wherein the retention member is configured to extend from the circumferential groove and press against the hanger bend portion to facilitate maintaining the hook member within the hook channel.
In another aspect, a turbine assembly is provided. The turbine assembly includes a hanger including an inner radial hanger bend portion that defines a hook channel therein and a fairing including an outer surface, a hook member extending from said outer surface to mate with said hook channel, and a groove defined in said outer surface such that a portion of said hanger bend portion is positioned between said groove and said hook member. The assembly also includes a retention member sized for insertion into said groove, wherein said retention member is configured to extend from said groove and press against said hanger bend portion to facilitate maintaining said hook member within said hook channel.
In yet another aspect, a method of limiting axial movement between a hanger and a fairing within a turbine assembly is provided. The method includes extending a bend portion of the hanger to define a receiving channel therein, extending a hook member from an outer surface of the fairing to mate with the receiving channel, defining a groove in the outer surface such that at least a portion of the hanger bend portion is positioned between the groove and the hook member, inserting a retention member into the groove, and extending the retention member from the groove to press against the hanger bend portion of the hanger to facilitate maintaining the hook member within the receiving channel.
BRIEF DESCRIPTION OF THE DRAWINGS
FIGS. 1-20 show exemplary embodiments of the assembly and method described herein.
FIG. 1 is a schematic perspective view of a turbine frame hanger and a collection of fairing sections (e.g., flow path components) according to an embodiment;
FIG. 2 is a schematic perspective view of a turbine frame hanger as it is mounted to a collection of fairing sections according to an embodiment;
FIG. 3 is a schematic cross-sectional view of a turbine frame hanger as it is mounted to a fairing section, according to an embodiment;
FIG. 4 is a schematic cross-sectional view of a turbine frame hanger as it is mounted to a fairing section, according to an embodiment;
FIG. 5 is a schematic cross-sectional view of a turbine frame hanger as it is mounted to a fairing section, according to an embodiment;
FIG. 6 is a schematic cross-sectional view of a turbine frame hanger as it is mounted to a fairing section, according to an embodiment;
FIG. 7 is a schematic cross-sectional view of a turbine frame hanger as it is mounted to a fairing section, illustrating a scalloped opening for receiving a retention member, according to an embodiment;
FIG. 8 is a schematic cross-sectional view of a turbine frame hanger as it is mounted to a fairing section, illustrating a retention member inserted through a scalloped opening, according to an embodiment;
FIG. 9 is a schematic perspective view of a turbine frame hanger as it is mounted to multiple fairing sections, illustrating a retention member inserted through a scalloped opening, according to an embodiment;
FIG. 10 is a schematic perspective view of a turbine frame hanger as it is mounted to multiple fairing sections, illustrating a retention member inserted through a scalloped opening, according to an embodiment;
FIG. 11 is a schematic perspective view of a multi-turn retention member, according to an embodiment;
FIG. 12 is a schematic perspective view of multiple segmented retainers, according to an embodiment;
FIG. 13 is a schematic perspective view of a single-layer, 360 degree retainer ring, according to an embodiment;
FIG. 14 is a schematic perspective view illustrating a single sectioned retainer having a wavy region, according to an embodiment;
FIG. 15 is a schematic perspective view of multiple fairings attached to a hanger utilizing both a single-layer, 360 degree retainer ring topped with a plurality of sectioned retainers having wavy regions, according to an embodiment;
FIG. 16 is a schematic perspective view of multiple fairings attached to a hanger utilizing both a single-layer, 360 degree retainer ring topped with a plurality of sectioned retainers having wavy regions, according to an embodiment;
FIG. 17 is a schematic perspective view of a segmented retainer having a wavy region, according to an embodiment;
FIG. 18 is a schematic perspective view of the wavy region of a segmented retainer, according to an embodiment;
FIGS. 19a through 19d illustrate various configurations of retention members for retaining a hanger to a plurality of fairings, according to an embodiment; and
FIG. 20 shows an exemplary tool for installing and removing the retention members shown in FIGS. 19a through 19d.
DETAILED DESCRIPTION OF THE INVENTION
FIG. 1 is a schematic perspective view of a hanger 100 positioned to abut a front end 102 of a collection of fairings 104 aligned in a circular fashion. The illustrated hanger 100 is shown with a plurality of apertures 106 extending through a front flange 108 for attaching the hanger 100 to a frame 110 of a turbine engine. As shown in FIG. 2, the hanger arm 112 of the hanger 100 has a hook channel 114 having a substantially j-shaped cross section, for receiving a fairing circumferential hook 116 of a fairing 104. About a bend portion 118 of the hanger arm 112 is located an annular flat surface 120 that lines up vertically with a fairing circumferential retainer groove 122 in the fairing 104 when the hanger 100 is positioned as shown, such that the hook channel 114 of the hanger 100 is mated with the circumferential hook 116 of the fairing 104. The retainer groove 122 is for receiving an axial retention member 124, which may be a continuous ring with a single break in it, a continuous ring that substantially comprises a spiral having multiple rotations, a series of segmented retainers, and combinations thereof. The retention member 124 is placed in the retainer groove 122 so that the retention member 124 prevents the fore and aft movement of the fairing 104, and the retention member 124 thereby prevents the hook channel 114 of the hanger 100 from separating from the circumferential hook 116 of the fairing 104. Although a fairing 104 is shown as the flow path component in these exemplary embodiments, it should be recognized by one skilled in the art that any flow path component could take the place of the fairing 104.
As shown in FIG. 3, mechanical entrapment of the hook channel 114 in the circumferential hook 116 of the fairing 104 is accomplished by placing the retention member 124 in the retainer groove 122. A c-clip 126 is then installed adjacent the retention member 124, wherein the c-clip 126 has a horizontal tab 128 extending away from the rear of the c-clip 126. When the c-clip 126 is fully engaged, the horizontal tab 128 is positioned to abut an outer surface 130 of the retention member 124 to facilitate restricting movement of retention member 124 within the retainer groove 122.
FIG. 4 illustrates an embodiment of the retention member 124 as described above, locked into a circumferential retainer groove 122 in a fairing 104. The retention member 124 shown is a single ply ring, having a fore to aft thickness slightly less than the fore to aft distance between the vertical walls of the circumferential retainer groove 122.
FIGS. 5 and 6 illustrate another embodiment of a turbine frame hanger lock assembly 10. In this embodiment, the retention member 124 is a double ply, spiral ring, having a 720 degree circumference. A hanger located circumferential retainer groove 132 is provided by extending the hanger 100 about the bend portion 118 of the hanger arm 112, so that the channel of the hanger located circumferential retainer groove 132 substantially mates with the channel 123 of the circumferential retainer groove 122 in the fairings 104.
FIGS. 7 through 10 illustrate a scalloped opening 134 in the forward side 136 of the hook channel 114 and the forward side 138 of the fairing. FIG. 9 illustrates the scalloped opening 134 and shows that the opening 134 has a predetermined width for receiving a first end 140 of a multi-turn retention member 142. The first end 140 of the multi-turn retention member 142 is inserted into the scalloped opening 134 and the multi-turn retention member 142 is fed around the circumference of the hanger 100, such that the retention member 124 is traveling in an enclosed groove 144. A second end 146 of the ring has a loop that prevents further insertion of the multi-turn ring 142 into the enclosed groove 144.
As shown in FIG. 10, the loop of the second end 146 is configured to be less than the width of the scalloped opening 134 so that the loop can be contained within the scalloped opening 134 when the multi-turn retention member 142 is fully inserted into the enclosed groove 144. FIG. 11 illustrates the configuration of the multi-turn retention member 142 having a spiral shape.
FIGS. 12 and 13 illustrate a hybrid retaining ring configuration including a first retaining ring 147 (as shown in FIG. 13) that extends one full circumference (approximately 360 degrees) around the enclosed groove 144. A bent portion 150 at one end of the first retaining ring 147 prevents the ring from being inserted too far into the enclosed groove 144 and facilitates removal of the first retaining ring 147 therefrom. A second set of segmented retainers 148 (as shown in FIG. 12) is then installed on top of the first retaining ring 147, such that each of the set of segmented retainers 148 extends around less than the full circumference of the channel. As illustrated in FIG. 12, each of the set of segmented retainers 148 extend a fraction of the circumference of the enclosed groove 144.
As shown in FIG. 14, each of the set of segmented retainers 148 can have a wavy region 152 (e.g., an axial wave) in them to axially preload the contents of the enclosed groove 144. In this case, the first retainer ring 147 is formed without wavy regions such that the first retainer ring 147 is substantially planar in the plane perpendicular to the axis around which the ring 147 extends. According to an embodiment, each segmented retainer 148 may include a ring layer 154 having a wavy region 152 positioned thereon. A spring clip 156 may be attached to one end of the ring layer 154 for preventing rigid body motion (e.g., circumferential motion). Finally, a spacer 158 is configured to attach the spring clip 156 to a top surface of the ring layer 154. According to another embodiment, each segmented retainer 148 may include a layer 154 having a wavy region 152, and an integrated spring clip 160.
In one embodiment, the sets of segmented retainers 148 is inserted into the channel as shown in FIGS. 15 and 16, through the scalloped openings 134, such that each segmented retainer 148 with a wavy region 152 axially preloads the channel, preventing axial (e.g., fore and aft) movement of the first retaining ring 147 and each of the segmented retainers 148. The interface between the hanger 100 and the fairings 104 forms the scalloped openings 134 such that there is one scalloped opening 134 formed when two fairings 104 are placed side-by-side and a hanger 100 is positioned adjacent the fairings 104, as shown in FIG. 15. The wavy region 152 of each of the set of segmented retainers 148 is illustrated in FIGS. 17 and 18.
FIGS. 19a through 19d illustrate various alternative configurations for retention members. In FIG. 19d, the continuous multi-turn retention member 124 is illustrated.
FIG. 19a illustrates a hybrid retention member configuration including a first retention member 162 that extends one full circumference around the channel, and a second set of segmented retainers 164 that are inserted through scalloped openings 134 adjacent the first retention member 162, such that each of the retention members 164 extend one quarter of the circumference of the hanger 100.
FIG. 19b illustrates a ring configuration including sixteen ring portions 166 that each extend one-sixteenth of the circumference of the hanger 100. Each ring portion 166 is inserted through a scalloped opening 134 to extend within the enclosed groove 144 until the loop 168 prevents further insertion.
FIG. 19c illustrates a retention configuration including four retention member portions 170 that each extend one-fourth of the circumference of the hanger 100. Each retention member portion 170 is inserted through a scalloped opening 134 to extend within the enclosed groove 144 until the loop 172 prevents further insertion.
FIG. 20 shows an X-shaped tool 174 for installing and removing a retention member 124 or segmented retainer. The X-shaped tool 174 has four advancing pins 176 for insertion into apertures 178 in the retention member 124 or segmented retainer. During installation of the retention member 124 or segmented retainer, a portion of the retention member 124 or segmented retainer is bent in the direction opposite the scalloped opening, until the retention member 124 or segmented retainer is fully installed in the scalloped opening. Because of this bend in the retention member 124 or segmented retainer, an advancing pin 176 of the X-shaped tool 174 can be inserted into a given aperture so that the X-shaped tool 174 is rotated in a counter clockwise manner, pushing the retention member 124 or segmented retainer into the scalloped opening. When a downstream aperture is nearly inserted into the scalloped opening, another of the advancing pins 176 engages an upstream aperture to continue installation. Once the entire retention member 124 or segmented retainer is inserted into the scalloped opening, the X-shaped tool 174 is removed. By reversing the direction of rotation of the X-shaped tool 174, a retention member 124 or segmented retainer can be removed from the scalloped opening.
Exemplary embodiments of a turbine hanger lock assembly and methods of assembling the turbine hanger lock assembly are described above in detail. The assembly and method are not limited to the specific embodiments described herein, but rather, components of the assembly and/or steps of the method may be utilized independently and separately from other components and/or steps described herein. Further, the described assembly components and/or the method steps can also be defined in, or used in combination with, other assemblies and/or methods, and are not limited to practice with only the assembly and/or method as described herein.
This written description uses examples to disclose the invention, including the best mode, and also to enable any person skilled in the art to make and use the invention. The patentable scope of the invention is defined by the claims, and may include other examples that occur to those skilled in the art. Such other examples are intended to be within the scope of the claims if they have structural elements that do not differ from the literal language of the claims, or if they include equivalent structural elements with insubstantial differences from the literal languages of the claims.
Patent Grant
10344621
