Machine mounting system

A gas turbine engine assembly includes a gas turbine engine mounted on a three-point mounting frame. The three-point mounting frame includes an engine support structure having first and second beams in a V-configuration, and a secondary support structure that is positioned about the engine support structure and has a rectangular footprint. The frame may include a Y-configuration that includes the V-configuration, and may be implemented in a machine mounting system, such as in a marine vessel.

TECHNICAL FIELD

The present disclosure relates generally to mounting apparatuses for Machines, such as gas turbine engines, and relates more particularly to a three-point Frame with first and second beams joined in a V-configuration.

BACKGROUND

Specialized mounting systems have been necessary for machines and all manner of mechanical devices since the dawn of the industrial era. It has been found that for relatively large, bulky machines such as certain engines, mounting systems must often be developed which can provide robust support and stability to the machine, while being tailored to specific machine designs. Mounting strategies often must further account for the environments in which a particular machine will operate.

The marine industry provides a number of examples of particular operating environments requiring specialized machine mounting systems to properly support large, heavy machines. This is due at least in part to the motion and vibrations typically experienced by marine vessels. An otherwise flat, generally planar vessel deck may experience torsional motion under the influence of wave action or other vibration and mechanical stresses, and in turn may transmit the torsional motion to the mounting systems for machines carried on the vessel. Many engine-driven components have a rectangular mounting format and, accordingly, many engine or other machine systems have four or more mounting points.

Due to such torsional motion, however, four-point mounting systems for onshore applications are typically not ideal for offshore systems. Twisting of a vessel's deck can cause the mounting points of a four-point system to actually move out of the originally intended mounting plane. For equipment having a low tolerance for misalignment of components, inadequate mounting can be fatal. In an attempt to address the above problems, engineers typically take a four-point mounting frame and simply mount it on three mounting members for marine applications. This approach, however, has drawbacks of its own.

In an aerospace context, one example of a specialized mounting system for an aircraft engine is known from U.S. Pat. No. 5,028,001 to Bender et al. Bender et al. describe a method for coupling an engine to a support frame which mounts to a fuselage of an aircraft. The method uses a three-point vibration isolating mounting system in which load reactive forces at each of the mounting points are statically and dynamically determined. A first vibration isolating mount pivotally couples a first end of a support beam to the engine, allowing a pivoting action therebetween. An opposite end of the supporting frame is coupled to the engine with a pair of vibration isolating mounts which are oriented such that they are pivotable about a circumference of the engine. While the design of Bender et al. certainly has useful applications, it appears to be engineered for a specific engine type, and thus suffers from lack of flexibility in its applications.

The present disclosure is directed to one or more of the problems or shortcomings set forth above.

SUMMARY OF THE DISCLOSURE

In one aspect, a three-point frame for a machine mounting system is provided. The three-point frame includes a machine support structure including first and second beams joined in a V-configuration. A secondary support structure having a rectangular configuration is positioned about the machine support structure.

In another aspect, the present disclosure provides a gas turbine engine assembly including a gas turbine engine, and a three-point mounting frame for the gas turbine engine. The three-point mounting frame includes an engine support structure having first and second beams in a V-configuration, and a secondary support structure positioned about the engine support structure with a rectangular footprint.

In still another aspect, the present disclosure provides a marine vessel having a marine vessel body. A gas turbine engine including a driver and at least one driven component is further provided. A three-point mounting frame is provided having an engine support structure with a first beam and a second beam joined in a V-configuration. Three mounting members are coupled with the frame.

DETAILED DESCRIPTION

Referring toFIG. 1, there is shown an engine assembly8, which may be a gas turbine engine assembly, according to the present disclosure. Assembly8includes a gas turbine engine driver component12and a driven component14, such as a compressor and gearbox having a rectangular mounting configuration. Driver component12and driven component14may be coupled with a machine mounting frame10. Frame10includes first and second beams22aand22bjoined in a V-configuration and defining a predetermined three-point load path, illustrated with vector arrows A1, A2and A3inFIG. 1.

Frame10may further be mounted to a mounting platform50, such as a marine vessel body, via mounting members (not shown inFIG. 1) positioned at points P1, P2and P3, defining a mounting plane R which is oriented parallel to beams22aand22b. When platform50experiences torsional stresses, points P1, P2and P3remain substantially within a common plane, although this plane may actually differ from plane R as torsional stresses cause movements such as twisting of platform50. The geometry and construction of frame10allows positioning of the mounting members at optimal load-bearing points between frame10and mounting platform50. The load path to mounting platform50is predetermined in that one of the three mounting points, P1inFIG. 1, will always lie along a centerline C of frame10bisecting the V-configuration formed by beams22aand22b. Similarly, the other mounting points, P2and P3inFIG. 1will lie generally proximate ends of beams22aand22bopposite the ends at which beams22aand22bare joined. The actual positions chosen for each of points P1, P2and P3may be adjusted to positions that are optimal for the load type, geometry and design of frame10.

It should be appreciated that while assembly8is particularly well-suited to a gas turbine engine assembly, the present disclosure is not thereby limited. Other machines or engine types such as reciprocating engines might be substituted for the gas turbine engine ofFIG. 1without departing from the scope of the present disclosure. Similarly, while driven component14may comprise a gearbox and a compressor, a wide variety of other driven components such as a pump, generator or driveshaft might be substituted for driven component14without departing from the intended scope of the present disclosure.

Beams22aand22bwill typically be coupled with a third beam20to form a machine support structure18having a Y-configuration that includes the aforementioned V-configuration. It is contemplated that machine support structure18will serve as a primary load carrying component of frame10, supporting much or all of the weight of gas turbine engine driver component12thereon. A secondary support structure24having a rectangular configuration and defining a rectangular footprint is positioned about machine support structure18and may be connected therewith via a plurality of lateral bulkheads36positioned at selected length positions of frame10. It is contemplated that secondary support structure24may support all or most of the weight of gas turbine engine driven component14, transferring the load to machine support structure18via bulkheads36, for example. The rectangular configuration of secondary support structure24allows driven components having a rectangular mounting configuration to be readily coupled with frame10.

Each of machine support structure18and secondary support structure24may be formed from standard metallic I-beams. With respect to machine support structure18, it may comprise first and second I-beams22aand22bcoupled together, and coupled to a third I-beam20at a first structural node34. Third beam20may actually comprise one, two or more I-beam sub-components joined at another structural node32. All of the I-beams, bulkheads and structural nodes making up frame10may be welded or bolted together, and may be formed from commercially available I-beams and/or bulkheads, or may be formed by welding together flat plates to create components having the desired configuration. Structural nodes32and34may comprise a different material than the various beams of frame10, and may be formed as separate modular pieces. Alternatively, nodes32and34may represent merely points where the respective components are joined together.

Referring also toFIG. 2, there is shown a sectioned end view of frame10taken along line2-2ofFIG. 1. As illustrated inFIG. 2, joining of beam20with secondary support structure24via bulkheads36may have the added benefit of providing for easily constructed fluid tanks21aand21b, one on each side of beam20. To form fluid tanks21aand21b, additional sheet stock may be welded to the underside of frame10to create tanks on each side and extending along the length of beam20, the structural members of frame10thereby serving as baffles for the fluid tanks. In such an embodiment, tanks21aand21bserve the additional purpose of providing torsion boxes for enhancing the stiffness of frame10. A fluid pump23may be disposed within one or both of tanks21aand21b.

Turning toFIG. 3, there is shown in perspective another embodiment of a frame110according to the present disclosure. Frame110is similar to frame10ofFIG. 1, but differs in that rather than being constructed as a unitary piece, three separate frame modules or frame units are used. In particular, a first module110aor first frame unit is provided which includes a portion of machine support structure118, a structural node132and a portion of rectangular support structure124. A second module110bor second frame unit is provided, including another portion of machine support structure118and another portion of rectangular support structure124, and another structural node134. Yet a third module110cor third frame unit is provided, including a portion of rectangular support structure124. The embodiment ofFIG. 3is contemplated to be particularly applicable in designs wherein it is desirable to adapt a length of frame110for driver and/or driven components having different lengths. For example, for gas turbine engines of different sizes, frame110could be constructed with an end module110aselected to have a size corresponding with that of the gas turbine engine. In other words, a plurality of modules might be manufactured, and a module having the desired length selected as module110a, allowing the frame design to be adapted for different size components. The use of structural nodes132and134is further contemplated to improve the fatigue life of joints within frame110. Embodiments are contemplated wherein structural nodes formed from one type of material are coupled with I-beam components formed of another type of material. The various modules/components of frame110ofFIG. 2, as well as the other frames described herein, may be assembled via a dry fit process using known tab joint systems, or by any other suitable process.

Turning now toFIG. 4, there is shown a marine cradle assembly208according to the present disclosure. Cradle assembly208includes a frame210, which may include a Y-configuration machine support structure (a third beam220is shown), and a secondary support structure224coupled therewith. Cradle assembly208differs from the foregoing described embodiments in that it may include a rail mounting design for sliding a package219into a desired mounting position on frame210. In particular, cradle assembly208may include first and second rails240aand240b, allowing a package such as an engine219to slide into a desired mounting position, in either of first and second slide directions A and A′. Cradle assembly208may further include an enclosure230having a sliding roof with first and second roof panels231aand231bmounted above frame210and slidable in sliding directions B and B′. In addition to enclosing package219, enclosure230further stiffens and strengthens cradle assembly208.

Referring also toFIG. 5, there is shown an end view of cradle assembly230ofFIG. 4. Similar to the embodiment described with respect toFIG. 1, first and second fluid tanks221aand221bwhich are integral with portions of frame210may be provided, and a pump223disposed therein. Frame210may be mounted on one or more gimbals225at one or more of the mounting points. Anti-vibration mounts may also be used, or a combination anti-vibration mount and gimbal as such are known in the art. The other three-point mounting systems of the present disclosure may similarly be mounted via gimbals, anti-vibration mounts or combination anti-vibration mounts and gimbals.

FIG. 5further illustrates another package212on top of package219. While the lower package219might be any type of machine mounted to frame210and within rails240aand240b, package219might also be another frame for mounting a gas turbine engine, e.g. package212. In other words, rather than sliding a gas turbine engine package within rails240aand240b, a frame might be slid therein, and the actual gas turbine engine components mounted thereon. Thus, frame210may serve as a sub-base to which another mounting frame may be coupled, for instance a driver frame and a driven component frame positioned on top of frame210. Such an embodiment facilitates retrofit applications wherein it is desirable to take an existing machine mounting system, for instance an onshore gas turbine engine assembly, and transfer the machine mounting system to an offshore environment. The base and sub-base concepts are also contemplated to be well-suited to particularly large and heavy applications, such as for heavier compressor installations.

While it is contemplated that cradle208may benefit through the use of enclosure230, the enclosure is not a critical component thereof. Similarly, although the use of mounting rails240aand240bis described in the context of cradle208, mounting rails might similarly be used with any of the other embodiments of the present disclosure described herein. Further still, while the sub-base concept is discussed in the context of marine cradle208, other embodiments of the present disclosure might be used as a sub-base, or in conjunction therewith.

Referring now toFIG. 6, there is shown yet another embodiment of the present disclosure including a three-point frame310. Frame310is similar to the foregoing embodiments, but differs in that it includes a “bridge” configuration for machine support structure318. In particular, in the embodiment ofFIG. 6, machine support structure includes first and second beams in a V-configuration, joined with a third beam320to define a Y-configuration. Each of the first and second beams includes a first portion322a,322b, respectively, and a second portion322cand322d, respectively. The respective first portions322aand322bmay be disposed substantially in the same plane with a central bridge portion327that is part of third beam320, whereas the respective second portions322cand322dmay angle downwardly relative to bridge portion327.

In frame310, it is possible to vertically position the secondary support structure324independently of the machine support structure. The sizing and shape of bulkheads336may be varied to alter the relative vertical positions of the respective frame components. In general, the bridging of the machine support structure serves to stiffen the overall structure of frame310, which is contemplated to be beneficial where mounting particularly heavy equipment.

Referring now toFIG. 7, there is shown yet another embodiment of a frame410according to the present disclosure. Frame410includes a machine support structure having first and second beams422aand422barranged in a V-configuration, and a rectangular support structure424positioned about machine support structure418. Frame410differs from other embodiments described herein in that the machine support structure is made up of only two beams. A plurality of bulkheads436connect machine support structure418with secondary support structure424.

INDUSTRIAL APPLICABILITY

Referring to the drawing Figures generally, frames10,110,210,310and410will all share the basic machine support structure having first and second beams in a V-configuration. The use of the V-configuration allows a predetermined three-point load path to a mounting platform such as a marine vessel body or other structure. Plane R will typically be oriented parallel a component mounting plane defined by secondary support structure24, and an engine mounting plane defined by machine support structure18. In certain embodiments, the component mounting plane or component mounting interface will be coplanar with the machine mounting plane or interface, whereas in other embodiments they may be non-coplanar to provide a multi-level frame or multi-level marine cradle.

When mounting platform50experiences torsional motion, for example, where a marine vessel deck comprising platform50twists, mounting points P2and P3may move relative to point P1. Frame10,110,210,310,410will typically be mounted at point P1via a rotatable mounting member such as the gimbal shown inFIG. 5, allowing the entire structure supported by the frame to rotate or rock back and forth at one end about its mounting point P1. Twisting of support platform50can thus take place without substantially disturbing the essentially planar configuration of the triangular mounting interface. This behavior differs from earlier, four-point machine mounting designs wherein two sets of mounting points at opposite ends of a machine mounting frame are by definition forced out of a mounting plane by torsional movement of the support platform.

The present disclosure thus provides a versatile, adaptable structural concept for machine mounting, in particular for offshore environments wherein the mounting support platform may be subjected to torsional movement. As described herein, the structural concepts of the present disclosure may include single level frames, multi-level frames, modular split frames and multi-frame base/sub-base structures. By combining a rectangular component interface with the overall V-configuration or Y-configuration concepts, many standard driven components which are configured for rectangular mounting may be easily coupled to and supported by the three-point mounting frames described herein. Still further variation may be achieved by adjusting the size, number, thickness and spacing of the bulkheads which connect the respective support structures. This flexibility provides a substantial advantage over many earlier designs wherein frames had to be custom built or modified to accommodate components not originally designed for offshore use. Moreover, frames according to the present disclosure have more consistent mounting forces than many earlier designs, allowing for optimum and consistent placement of additional mounting hardware such as the gimbals and/or anti-vibration mounts described herein. Where these concepts are implemented in the context of a marine cradle, machines designed for onshore use such as gas turbine engine assemblies and driven components can be easily integrated into offshore applications.

The present description is for illustrative purposes only, and should not be construed to narrow the breadth of the present disclosure in any way. Thus, those skilled in the art will appreciate that various modifications might be made to the presently disclosed embodiments without departing from the intended spirit and scope of the present disclosure. For instance, while it is contemplated that the machine support structure will typically be somewhat more robust than the secondary support structure, this need not be the case. For example, rather than the relatively thinner structural components of secondary support structure24shown inFIG. 1, larger, thicker beams might be used to accommodate relatively heavier driven components or more than one driven component. The rectangular support structure might also be connected with one or more of the three mounting members, depending on the application. Further still, while the present description discusses assembling various selected modules to arrive at the fully constructed frame, other portions of the frame might be formed as modular units than the specific modular units described herein. For instance, each of the described structural nodes might be coupled with one or more of the beams of the machine support structure to form separate modules. These modules could then be custom combined with portions of the secondary support structure. Other aspects, features and advantages will be apparent upon an examination of the attached drawing Figures and appended claims.