Patent Application
20150224611
This application claims priority to European patent application No. EP14461508.5, entitled “METHOD AND SYSTEM FOR NON-INVASIVE SEPARATION OF COMPONENTS,” filed Feb. 10, 2014, the disclosure of which is incorporated herein by reference in its entirety.
The present disclosure relates to the assembly and disassembly of components, and particularly to the separation or joining of heavy components, such as the halves of steam and gas turbine engine housings.
At least some known gas turbine engines include at least a compressor section, a combustor section, and a turbine section. At least some known steam turbine engines include at least one of a high pressure section, a medium pressure section, and a low pressure section. In at least some known gas and steam turbine engines, one or more of these sections typically includes a housing formed with upper and lower halves that join along a horizontally-extending interface. In at least some known housings for gas and steam turbine engines, the upper and lower halves may be massive, weighing several hundreds or even several thousands of pounds. For safety and stability, the lower halves of the housings may be secured to a floor or underlayment, for example via bolts. In the housings for at least some gas and steam turbine engines, the upper and lower halves include flanges that define the interface. Over time, due to the weight of the housing upper half, scaling, distortion, oxidation, and/or other phenomena, the flanges of the upper and lower halves may become adhered to one another, for example, via microwelding. In at least some known housings for gas and steam turbine engines, the respective halves of the housings may include vertically-extending portions that are in surface-to-surface contact with each other, and which likewise may become adhered to one another.
Periodically, it may be desirable or necessary to separate the halves of a gas or steam turbine engine housing, for example for repair, routine maintenance or installation of upgrades. The upper halves of at least some known gas and steam turbine engine housings are provided with lifting structures, such as eyebolts, to which a lifting device, such as a crane or winch, may be attached, to lift the housing upper half off of and away from the housing lower half. However, adhesion between juxtaposed surfaces along the interface between the halves, or along interfaces within the housing, may create a resistive force that must be overcome, that is far in excess of the force required to lift the weight of the upper half of the housing. Moreover, the resistive force may be far in excess of the capacity of the lifting structures provided on the housing upper half. Accordingly, in at least some known gas and steam turbine engine housings, additional lifting structures may be attached, on an ad hoc basis, to the upper housing half, to provide sufficient locations to which lifting devices can be coupled, to enable sufficient lifting force to be applied to the upper half. Such additional lifting structures may be attached to the housing upper halves by invasive techniques, including but not limited to welding and drilling.
In an aspect, a method for use in facilitating relative movement between first and second components is provided. The method includes inserting a first component engagement assembly into an opening defined in the first component, wherein the first component engagement assembly is threadably coupled adjacent to a first end of a thrust member such that the thrust member extends through the first component opening and a second end of the thrust member extends toward the second component. The method also includes coupling the first component engagement assembly in frictional engagement with an inner surface of the first component opening. The method also includes exerting torque on the thrust member to cause the thrust member to move relative to the first component engagement assembly to exert, via the second end of the thrust member, one of a thrust force and a traction force against the second component to move the second component relative to the first component.
In another aspect, a system for facilitating relative movement between first and second components is provided. The system includes a thrust member. The system also includes a first component engagement assembly threadably coupled adjacent to a first end of the thrust member. The first component engagement assembly is configured for insertion into an opening defined in the first component such that the thrust member extends through the first component opening and a second end of the thrust member extends toward the second component. The first component engagement assembly is configured to facilitate frictional engagement with an inner surface of the first component opening. The thrust member is also configured to move relative to the first component engagement when torque is exerted on the thrust member. The thrust member is also configured to exert, via the second end of the thrust member, one of a thrust force and a traction force against the second component to move the second component relative to the first component.
In another aspect, a turbine system is provided. The turbine system includes at least a turbine section. The turbine system also includes a component engagement system for facilitating relative movement between first and second components in at least the turbine section. The component engagement system includes a thrust member. The component engagement system also includes a first component engagement assembly threadably coupled adjacent to a first end of the thrust member. The first component engagement assembly is configured for insertion into an opening defined in the first component such that the thrust member extends through the first component opening and a second end of the thrust member extends toward the second component. The first component engagement assembly is configured to facilitate frictional engagement with an inner surface of the first component opening. The thrust member is also configured to move relative to the first component engagement when torque is exerted on the thrust member. The thrust member is also configured to exert, via the second end of the thrust member, one of a thrust force and a traction force against the second component to move the second component relative to the first component.
Although specific features of various embodiments of the disclosure may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of the disclosure, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing. As used herein, “through-bores” and “blind bores” may collectively be referred to as “openings.” Also, as used herein, the term “couple” is not limited to a direct mechanical, thermal, communication, and/or an electrical connection between components, but may also include an indirect mechanical, thermal, communication and/or electrical connection between multiple components.
The present disclosure relates to methods and systems for separating components in machinery, such as, but not limited to housing halves for gas and steam turbine engines. Housing halves for heavy machinery such as the housings for gas and steam turbine engines used for power generation may be massive, weighing hundreds or thousands of pounds. Over time, such housing halves may become adhered to each other, through one or more of the mechanisms previously described herein. The present disclosure relates to methods and systems that will enable halves of housings, or any other pairs of joined components, that have become adhered to each other to be separated without resorting to invasive attachment of additional lifting structures or other separation structures. The methods and systems described herein also facilitate the separation of components in orientations other than those in which the components are joined along a horizontal interface. The methods and systems described herein may also facilitate the coupling of components.
In operation, air 103 flows through compressor section 102, and after compression, is supplied to combustor section 104. Fuel 105 is channeled to a combustion region and/or zone (not shown) that is defined within combustor section 104 wherein the fuel is mixed with the air and ignited. Combustion gases generated are channeled to turbine section 108 wherein gas stream thermal energy is converted to mechanical rotational energy. Turbine section 108 is coupled to rotor 110, for rotation about an axis 106. In the exemplary embodiment, system 101 includes a load 112 that is coupled to rotor 110. Load 112 may be any device or system that uses rotational input from gas turbine engine 100, via rotor 110, to function. For example, load 112 may be, but is not limited to, an electrical generator.
In the exemplary embodiment, gas turbine engine 122 and steam turbine engine 124 may be each mechanically coupled to electric power generators 126 and 128, respectively. System 121 may also include at least a steam boiler 130 that is coupled in flow communication with gas turbine engine 122 via exhaust gas conduit 131. Steam turbine engine 124, in the exemplary embodiment, includes a high-pressure (“HP”) section 153, an intermediate-pressure (“IP”) section 154, and a low-pressure (“LP”) section 156. In the exemplary embodiment, an HP steam conduit 158 extends from a HP steam section (not shown) in boiler 130 to HP section 153. Similarly, an IP steam conduit 162 extends from an IP steam section (not shown) in boiler 130 to IP section 154, and an LP steam conduit 164 extends from an LP steam section (not shown) in boiler 130 to LP section 156. In the exemplary embodiment, system 121 also includes a control system 170 coupled to boiler 130, and to a steam turbine or process control system 175 that is configured to detect operating parameters or conditions within each of HP section 153, IP section 154, and LP section 156 of steam turbine engine 124.
Component engagement system 250 includes a thrust member 260. In the exemplary embodiment, thrust member 260 is in the form of a threaded bolt. In an alternative embodiment, thrust member 260 may have any configuration that enables component engagement system 250 to function as described herein. Component engagement system 250 also includes a nut 264, and a non-threaded collar 255 that is slidably coupled around bolt 260. Bolt 260 includes a head 251 and a threaded shaft 262. As described in further detail hereinbelow, bolt 260 facilitates the exertion of a thrusting force between halves 202 and 204, and more specifically, between flanges 206 and 208. In the exemplary embodiment, component engagement system 250 also includes a plurality of first jaws 256 and an internally-threaded first cone 258.
As shown in further detail in
As previously described, component engagement system 250 is installed into section 200 by inserting component engagement system 250 into through-bore 252 of flange 206, and further into blind bore 254 of flange 208 (all shown in
Prior to actuation of components separation system 250, as described herein, a gap 259 (shown in
As illustrated in
Continued rotation of bolt 260 while force is exerted downwardly on bolt 260 eventually generates sufficient reaction force to overcome the adhesion forces maintaining flanges 206 and 208 in contact, and flanges 206 and 208 will separate, as shown in
In an alternative embodiment, instead of a circular cross-section, first cone 258 may be provided with a polygonal cross-section (not shown), to provide a plurality of substantially planar outer surfaces 267. In this alternative embodiment, inner surfaces 257 of first jaws 256 likewise may be substantially planar, to engage with planar outer surfaces 267. In another alternative embodiment, each of first cone 258 and first jaws 256 may have any suitable configuration that enables first cone 258 to function as a wedge member, such that when first jaws 256 and first cone 258 are brought together, as described hereinabove, first cone 258 exerts a lateral force on first jaws 256 that tends to force first jaws 256 apart and against inner surface 249 of through-bore 252.
As previously described, component engagement system 250 is configured for use with pre-existing openings provided in housing halves 202 and 204, specifically, through-bore 252 defined in flange 206 and blind bore 254 defined in flange 208. In an alternative embodiment, bores 252 and 254 may be specifically provided for use with component engagement system 250, and may be defined within flanges 206 and 208 before or after assembly of gas turbine engine 100 (shown in
In the exemplary embodiment, a plurality of component engagement systems 250 are deployed along interface 226 (shown in
In the exemplary embodiment, a penetrant and/or lubricant material may be applied to interface 226 to facilitate separation of flanges 206 and 208, provided that care is taken to ensure that no such material enters bores 252 and 254 to compromise the frictional engagement between first jaws 256 and inner surface 249. In an alternative embodiment, separation of flanges 206 and 208 is performed without the use of a penetrant and/or lubricant material.
Accordingly, component engagement system 300 is configured for insertion into a first through-bore (not shown) defined in a first flange of a housing upper half and further into a second through-bore (not shown) defined in a flange of an adjacent housing lower half, wherein the first and second through-bores are substantially coaxially oriented with respect to each other. Component engagement system 300 includes a thrust member 301. In the exemplary embodiment, thrust member 301 is in the form of a double-threaded bolt. In an alternative embodiment, thrust member 301 may have any suitable configuration that enables component engagement system 300 to function as described herein. Component engagement system 300 also includes a first component engagement assembly 314 and a second component engagement assembly 330. Bolt 301 includes a shaft 302, a head 304, a first end 306 and a second end 308. In the exemplary embodiment, first end 306 includes threads 310 having a first pitch and a first direction sense (for example, right-handed), while second end 308 includes threads 312 having a second pitch which may be the same as the first pitch, and a second direction sense opposite to the first direction sense (that is, left-handed). Threads 310 transition into threads 312 at about midway along shaft 302, as indicated by a line 313.
In an alternative embodiment, threads 310 and 312 may have any pitch and/or sense of direction that enables component engagement system 300 to function as described herein. In addition, bolt 301 may be fabricated from any suitable material and/or have any suitable configuration that enables component engagement system 300 to function as described herein. For example, shaft 302 and head 304 may be initially fabricated as separate elements, to enable first component engagement assembly to be coupled onto shaft 302, and then head 304 may be secured to shaft 302 using any suitable method, including but not limited to welding, that enables torque applied to head 304 to be transmitted to shaft 302.
In the exemplary embodiment, first component engagement assembly 314 includes a nut 316, a collar 318, first jaws 320, and a first cone 322 that is internally-threaded (not shown) to threadably engage threads 310 of shaft first end 306. First jaws 320 are coupled around shaft 302 by one or more spring rings 324 oriented in grooves 326 defined in first jaws 320. In the exemplary embodiment, nut 316, collar 318, first jaws 320, first cone 322, and spring rings 324 may have the same configurations and functions as nut 264, collar 255, first jaws 256, first cone 258, and spring rings 245, respectively, that are described hereinabove and shown in
In the exemplary embodiment, second component engagement assembly 330 includes a nut 332, a collar 334, second jaws 336, and a second cone 338 that is internally-threaded (not shown) to threadably engage threads 312 of shaft second end 308. Second jaws 336 are coupled around shaft 302 by one or more spring rings 340 oriented in grooves 342 defined in second jaws 336. In the exemplary embodiment, nut 332, collar 334, second jaws 336, second cone 338, and spring rings 340 may have the same configurations and functions as nut 264, collar 255, first jaws 256, first cone 258, and spring rings 245, respectively, that are described hereinabove and shown in
Use of component engagement system 300 to separate two housing halves, such as halves 202 and 204 (shown in
During continued rotation of bolt 301, component engagement assemblies 314 and 330 force the flanges coupled to them (not shown) to be separated, as previously described with respect to component engagement system 250 described hereinabove. In the exemplary embodiment, any number of component engagement systems 300 may be installed in a housing (not shown) that enables component engagement systems 300 to function as described herein. Similar to component engagement system 250, component engagement system 300 facilitates separation of housing halves that are adhered together, eliminating the need to attach additional coupling and lifting structures to either of the housing halves. In addition, the use of component engagement system 300 facilitates the application of separation forces to adhered-together housing portions in a controlled, incremental manner via the use of threaded bolt 301 and cones 322 and 338.
Component engagement system 300 may also be used, in a reverse procedure to that described hereinabove, to close a gap between flanges 206 and 208 (shown in
The methods and systems described herein address at least some of the disadvantages of, and provide advantages over, known component separation methods and systems. For example, the methods and systems described herein facilitate separation of adhered-together housing components without the need for intrusive coupling of purpose-built attachment and lifting devices to existing housings. In addition, the methods and systems described herein enable the application of separation forces to adhered-together housing components in a controlled, incremental manner. The methods and systems described herein enable the separation of adhered-together components that are horizontally coupled, vertically coupled, or in any other orientation. The methods and systems described herein also facilitate closure of a gap between two components that are being assembled.
Exemplary embodiments of systems and methods for separating components are described above in detail. The systems and methods are not limited to the specific embodiments described herein, but rather, actions of the methods and/or components of the systems may be utilized independently and separately from other components and/or actions described herein. For example, the systems and methods described herein are not limited to practice only with gas turbine engine systems, but also may be used in combination with any other devices that include housing halves or other components that may need to be separated or disassembled, for which assistance in exerting separating force would be useful.
It will be appreciated that the above embodiments that have been described in particular detail are merely example or possible embodiments, and that there are many other combinations, additions, or alternatives that may be included.
Although specific features of various embodiments of the disclosure may be shown in some drawings and not in others, this is for convenience only. In accordance with the principles of the disclosure, any feature of a drawing may be referenced and/or claimed in combination with any feature of any other drawing.
This written description uses examples to disclose the claimed subject matter, including the best mode, and also to enable any person skilled in the art to practice the claimed subject matter, including making and using any devices or systems and performing any incorporated methods. The patentable scope of the subject matter described herein 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.
While the disclosure has been described in terms of various specific embodiments, those skilled in the art will recognize that the disclosure may be practiced with modifications within the spirit and scope of the claims.
| Number | Date | Country | Kind |
|---|---|---|---|
| 14461508.5 | Feb 2014 | EP | regional |
