Patent Grant
9133724
The subject matter disclosed herein relates to the art of turbomachines and, more particularly, to a cover plate for a turbomachine component.
Many turbomachines include a compressor portion linked to a turbine portion through a common compressor/turbine shaft or rotor and a combustor assembly. The compressor portion guides a compressed air flow through a number of sequential stages toward the combustor assembly. In the combustor assembly, the compressed air flow 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 the turbine portion creating work that is output, for example, to power a generator, a pump, or to provide power to an aircraft. In addition to providing compressed air for combustion, a portion of the compressed airflow is passed through the turbine portion for cooling purposes.
The portion of the compressed airflow for cooling purposes often times flows through components that are exposed to the hot gases. Accordingly, many turbomachine components include internal passageways that provide conduits for the cooling airflow. Generally the components are formed with the internal passages from various super alloy materials and then provided with additional structure such as cover plates, baffles, or the like that either prevents or channels cooling airflow in a particular manner. The additional structure is typically welded to the component.
According to one aspect of the exemplary embodiment, a turbomachine component includes a body having a first end that extends to a second end. One of the first and second ends includes a mounting element, and a mounting component. A cover plate is arranged at the one of the first and second ends to establish an interface region. The cover plate includes a mounting member configured to align with the mounting element, and a mounting portion configured to align with the mounting element. A fastener member is configured and disposed to cooperate with the mounting element and the mounting member to constrain the cover plate to the body along at least two axes with the interface region being devoid of a metallurgical bond.
According to another aspect of the exemplary embodiment, a method of joining a cover plate to a turbomachine component without welding includes positioning the cover plate on the turbomachine component, aligning an opening formed in a mounting element provided on the turbomachine component with an opening formed on a mounting member provided on the cover plate to establish a fastener passage, and inserting a fastener through the fastener passage to constrain the cover plate to the turbomachine component along at least two axes.
According to yet another aspect of the exemplary embodiment, a turbomachine system includes a compressor portion, a turbine portion mechanically linked to the compressor portion, a combustor assembly fluidly connected to the compressor portion and the turbine portion, and a turbomachine component operatively associated with one of the compressor portion, the turbine portion and the combustor assembly. The turbomachine component includes a body having a first end that extends to a second end. One of the first and second ends includes a mounting element, and a mounting component. A cover plate is arranged at the one of the first and second end to establish an interface region. The cover plate includes a mounting member configured to align with the mounting element, and a mounting portion configured to align with the mounting element. A fastener member is configured and disposed to cooperate with the mounting element and the mounting member to constrain the cover plate to the body along at least two axes with the interface region being devoid of a metallurgical bond.
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.
With reference to
In the exemplary embodiment shown, turbine portion 6 includes a turbine housing 19 within which are disposed first, second, third, and fourth stages 20-23 that extend along gas path 18. Of course it should be understood that the number of stages in turbine portion 6 could vary. First stage 20 includes a plurality of first stage stators or nozzles, one of which is indicated at 30 arranged in an annular array, and a plurality of first stage buckets or blades, one of which is indicated at 32, mounted to a first stage rotor wheel 34. Second stage 21 includes a plurality of second stage stators or nozzles, one of which is indicated at 37 arranged in an annular array, and a plurality of second stage buckets or blades, one of which is indicated at 39, mounted to a second stage rotor wheel 41. Third stage 22 includes a plurality of third stage stators or nozzles, one of which is indicated at 44 arranged in an annular array, and a plurality of third stage buckets or blades, one of which is indicated at 46, mounted to a third stage rotor wheel 48. Fourth stage 23 includes a plurality of fourth stage stators or nozzles, one of which is indicated at 51 arranged in an annular array, and a plurality of fourth stage buckets or blades, one of which is indicated at 53, mounted to a fourth stage rotor wheel 55. Turbomachine 2 is also shown to include a plurality of inter-stage seal members 60, 62, and 64 arranged between adjacent ones of first, second, third, and fourth stages 20-23. As best shown in
In accordance with an exemplary embodiment, stator 37 includes a cover plate 110 that is secured to second end 84 defining an interface region (not separately labeled). Cover plate 110 may serve as an interface to turbine housing 19, or cover cooling passages (not shown) formed in stator 37. Cover plate 110 includes a body 117 having first and second opposing end sections 119 and 120 that are joined by first and second opposing edge sections 121 and 122. Cover plate 110 includes first and second mounting members 130 and 131 that take the form of first and second openings 132 and 133 formed in first edge section 119. In addition to mounting members 130 and 131, cover plate 110 includes first and second mounting portions 134 and 135. Mounting portions 134 and 135 constitute first and second angled surface portions 136 and 137 provided at first and second end sections 119 and 120 respectively. Angled surface portions 136 and 137 are configured to nest with angled surface sections 95 and 96 as will be discussed more fully below.
In further accordance with the exemplary embodiment, cover plate 110 is constrained to second end 84 of stator 37 along three axes. More specifically, cover plate 110 is positioned upon second end 84 such that mounting portions 134 and 135 nest with mounting components 93 and 94 and mounting members 130 and 131 register with mounting elements 89 and 90. Mounting members 130 and 131 are considered to register with mounting elements 89 and 90 when first and second openings 132 and 133 formed in first edge section 119 align with first and second openings 91 and 92 of mounting elements 89 and 90 to form corresponding first and second fastener passages (not separately labeled).
At this point, first and second fasteners 140 and 141 are inserted into the first and second fastener passages. One of fasteners 140 and 141 is formed to pass into one of the first and second fastener passages with a first tolerance and the other of fasteners 140 and 141 are formed to pass into the other of the first and second fastener passages with a second tolerance that is distinct from the first tolerance. For example, first fastener 140 may have a slightly looser fit in the first fastener passage then does second fastener 141 in the second fastener passage. The difference in tolerances allow for different rates of thermal expansion of nozzle 37 and cover plate 110 as well as manufacturing tolerances that may lead to minor misalignments in forming the first and second fastener passages.
At this point it should be understood that the cover plate in accordance with the exemplary embodiment is constrained to the second end of the stator along three distinct axes. That is, the fasteners constrain the cover plate to the stator along two axes and the mating angled surfaces provide retention along a third axes. Thus, the present invention describes a system of joining turbomachine components without the need for welding. Joining without welding allows for improved assembly and disassembly operations thereby easing manufacturing and service. The lack of welding also reduces costs and complications associated with welding dissimilar metals, super alloys and the like. It should be further understood that while shown mounted to a stator, the cover plate and method of attachment can be employed in connection with various other turbomachine components arranged along the gas path or in a wheel space of the turbomachine.
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.
| Number | Name | Date | Kind |
|---|---|---|---|
| 4187054 | Landis, Jr. et al. | Feb 1980 | A |
| 5120192 | Ohtomo et al. | Jun 1992 | A |
| 5197852 | Walker et al. | Mar 1993 | A |
| 5320483 | Cunha et al. | Jun 1994 | A |
| 5609466 | North et al. | Mar 1997 | A |
| 6142730 | Tomita et al. | Nov 2000 | A |
| 6217279 | Ai et al. | Apr 2001 | B1 |
| 6227798 | Demers et al. | May 2001 | B1 |
| 6382906 | Brassfield et al. | May 2002 | B1 |
| 6383602 | Fric et al. | May 2002 | B1 |
| 6386825 | Burdgick | May 2002 | B1 |
| 6418618 | Burdgick | Jul 2002 | B1 |
| 6530744 | Liotta et al. | Mar 2003 | B2 |
| 6761529 | Soechting et al. | Jul 2004 | B2 |
| 6769865 | Kress et al. | Aug 2004 | B2 |
| 6843479 | Burdgick | Jan 2005 | B2 |
| 6877952 | Wilson | Apr 2005 | B2 |
| 6884026 | Glynn et al. | Apr 2005 | B2 |
| 6932568 | Powis et al. | Aug 2005 | B2 |
| 6984101 | Schiavo, Jr. | Jan 2006 | B2 |
| 7008185 | Peterman et al. | Mar 2006 | B2 |
| 7029228 | Chan et al. | Apr 2006 | B2 |
| 7044709 | Bruce et al. | May 2006 | B2 |
| 7056084 | Nagane et al. | Jun 2006 | B2 |
| 7252481 | Stone | Aug 2007 | B2 |
| 7278820 | Keller | Oct 2007 | B2 |
| 7494317 | Keller et al. | Feb 2009 | B2 |
| RE40658 | Powis et al. | Mar 2009 | E |
| 7534086 | Mazzola et al. | May 2009 | B2 |
| 7918024 | Mooney, Jr. et al. | Apr 2011 | B2 |
| 20020028134 | Burdgick | Mar 2002 | A1 |
| 20020182057 | Liotta et al. | Dec 2002 | A1 |
| 20020187040 | Predmore | Dec 2002 | A1 |
| 20050244267 | Coign et al. | Nov 2005 | A1 |
| 20060053798 | Hadder | Mar 2006 | A1 |
| 20060062673 | Coign et al. | Mar 2006 | A1 |
| 20060073011 | Lee et al. | Apr 2006 | A1 |
| 20060171812 | Albrecht et al. | Aug 2006 | A1 |
| 20070009349 | Ward et al. | Jan 2007 | A1 |
| 20070237624 | Nigmatulin | Oct 2007 | A1 |
| 20080087021 | Radonovich et al. | Apr 2008 | A1 |
| 20080089780 | Erickson et al. | Apr 2008 | A1 |
| 20080152488 | Kammel et al. | Jun 2008 | A1 |
| 20100011773 | Suleiman et al. | Jan 2010 | A1 |
| 20100068041 | Nigmatulin et al. | Mar 2010 | A1 |
| 20100104426 | Keller et al. | Apr 2010 | A1 |
| 20100278631 | Heda et al. | Nov 2010 | A1 |
| 20100281879 | Shapiro et al. | Nov 2010 | A1 |
| 20100284800 | Sewall et al. | Nov 2010 | A1 |
| 20110014045 | McCall | Jan 2011 | A1 |
| 20110014054 | Nagler et al. | Jan 2011 | A1 |
| 20110044803 | Di Paola et al. | Feb 2011 | A1 |
| 20110229305 | Bergman et al. | Sep 2011 | A1 |
| 20130177384 | Coign et al. | Jul 2013 | A1 |
| Number | Date | Country |
|---|---|---|
| 1164252 | Dec 2001 | EP |
| 1262634 | Dec 2002 | EP |
| 2366873 | Sep 2011 | EP |
| 61066802 | Apr 1986 | JP |
| Entry |
|---|
| Search Report and Written Opinion from EP Application No. 13150157.9 dated Mar. 19, 2013. |
| Number | Date | Country | |
|---|---|---|---|
| 20130177408 A1 | Jul 2013 | US |
