US20180017466A1 - Systems and methods for attaching a probe to a casing of a gas turbine engine - Google Patents
Systems and methods for attaching a probe to a casing of a gas turbine engine Download PDFInfo
- Publication number
- US20180017466A1 US20180017466A1 US15/716,797 US201715716797A US2018017466A1 US 20180017466 A1 US20180017466 A1 US 20180017466A1 US 201715716797 A US201715716797 A US 201715716797A US 2018017466 A1 US2018017466 A1 US 2018017466A1
- Authority
- US
- United States
- Prior art keywords
- probe
- bayonet
- casing
- bayonet slot
- receptacle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Abandoned
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Classifications
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/14—Testing gas-turbine engines or jet-propulsion engines
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
- F01D17/02—Arrangement of sensing elements
-
- G—PHYSICS
- G01—MEASURING; TESTING
- G01D—MEASURING NOT SPECIALLY ADAPTED FOR A SPECIFIC VARIABLE; ARRANGEMENTS FOR MEASURING TWO OR MORE VARIABLES NOT COVERED IN A SINGLE OTHER SUBCLASS; TARIFF METERING APPARATUS; MEASURING OR TESTING NOT OTHERWISE PROVIDED FOR
- G01D11/00—Component parts of measuring arrangements not specially adapted for a specific variable
- G01D11/30—Supports specially adapted for an instrument; Supports specially adapted for a set of instruments
Definitions
- an operator may rotate the probe 102 until the bayonet 146 finds the opening 124 to the bayonet slot 120 so that the bayonet slot 120 may capture the bayonet 146 .
- This operation can be done blindly, i.e., strictly by feel.
- the operator may push down on the probe 102 in the axial direction to overcome the spring 130 in the probe receptacle 108 .
- the spring rate of the spring 130 may be high enough to prevent accidental (or unintended) disengagement but also low enough that the operator can overcome the spring 130 during installation and removal.
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- Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Gasket Seals (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
A system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore adjacent to the bayonet slot, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.
Description
- The disclosure generally relates to a probe and more particularly relates to systems and methods for attaching a probe to a casing of a gas turbine engine.
- Attaching probes to a casing of a gas turbine engine can be problematic, particularly when threading the probe into the casing where limited space is available and/or the line of sight is obstructed. For example, threading a probe into a threaded probe receptacle can be very difficult to do if the probe is very long. Anytime a threaded connection is used, there is a possibility of cross-threading. If cross-threading occurs in the probe receptacle, it may not be accessible for repair. Similarly, there is a possibility of the threads seizing. If seizing occurs, the probe may be indefinitely stuck in the probe receptacle and may not be accessible for repair. Threaded connections can also back-out, causing structural issues and/or leaks. Moreover, with threaded connections, it is often difficult to precisely position the probe.
- Some or all of the above needs and/or problems may be addressed by certain embodiments disclosed herein. In one embodiment, a system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.
- In another embodiment, a system for attaching one or more instruments to a casing of a gas turbine engine is disclosed. The system may include a probe. The system also may include a probe receptacle attachable to the casing. The probe receptacle may include an internal bore, a bayonet slot, a spring disposed within the internal bore, and a sealing surface within the internal bore. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include at least one bayonet positionable within the bayonet slot and a seal positionable adjacent to the sealing surface within the internal bore.
- In another embodiment, a system for attaching a probe to a casing of a gas turbine engine is disclosed. The system may include a probe receptacle attachable to the casing. The probe receptacle may include a casing seal portion attachable to the casing, a main body attachable to the casing seal portion, and a cap attachable to the main body. The cap may include a bayonet slot and a spring. The main body may include a sealing surface. The system also may include a probe attachment assembly disposed about the probe and configured to engage the probe receptacle. The probe attachment assembly may include a busing and seal disposed about the probe. The bushing may include at least one bayonet positionable within the bayonet slot. The seal may be positionable adjacent to the sealing surface.
- Other features and aspects of the systems and methods disclosed herein will be apparent or will become apparent to one with skill in the art upon examination of the following figures and the detailed description. All other features and aspects, as well as other system, method, and assembly embodiments, are intended to be included within the description and are intended to be within the scope of the accompanying claims.
- The detailed description is set forth with reference to the accompanying drawings. The use of the same reference numerals may indicate similar or identical items. Various embodiments may utilize elements and/or components other than those illustrated in the drawings, and some elements and/or components may not be present in various embodiments. Elements and/or components in the figures are not necessarily drawn to scale. Throughout this disclosure, depending on the context, singular and plural terminology may be used interchangeably.
-
FIG. 1 schematically depicts a system in accordance with one or more embodiments of the disclosure. -
FIG. 2 schematically depicts a probe receptacle in accordance with one or more embodiments of the disclosure. -
FIG. 3 schematically depicts a probe receptacle in accordance with one or more embodiments of the disclosure. -
FIG. 4 schematically depicts a probe receptacle in accordance with one or more embodiments of the disclosure. -
FIG. 5 schematically depicts a probe attachment assembly in accordance with one or more embodiments of the disclosure. -
FIG. 6 schematically depicts a probe attachment assembly in accordance with one or more embodiments of the disclosure. -
FIG. 7 schematically depicts a system in accordance with one or more embodiments of the disclosure. -
FIG. 8 schematically depicts a system in accordance with one or more embodiments of the disclosure. -
FIG. 9 schematically depicts a system in accordance with one or more embodiments of the disclosure. -
FIGS. 1-9 schematically depict various embodiments of asystem 100 for attaching aprobe 102 to acasing 104 of agas turbine engine 106. In some instances, theprobe 102 may be positioned downstream of a combustor of thegas turbine engine 106. Thesystem 100 may be used at any location about thegas turbine engine 106. - Generally speaking, the
system 100 may include aprobe receptacle 108 and aprobe attachment assembly 110. Theprobe receptacle 108 may be attached to thecasing 104 of thegas turbine engine 106. In some instances, theprobe receptacle 108 may be embedded within thecasing 104. As depicted inFIGS. 2 and 3 , theprobe receptacle 108 may include amain body 112, acasing seal portion 114, and/or acap 116. Thecap 116 may be attached to themain body 112 opposite thecasing seal portion 114. Thecap 116 andcasing seal portion 114 may be threaded or the like to themain body 112. Moreover, thecap 116, themain body 112, and/or thecasing seal portion 114 may be attached to thecasing 104 of thegas turbine engine 106. For example, thecap 116, themain body 112, and/or thecasing seal portion 114 may be threaded into thecasing 104. In some instances, theprobe receptacle 108 may be embedded within thecasing 104 or formed as an integral component of thecasing 104. Thecasing seal portion 114 may form a seal between theprobe receptacle 108 and thecasing 104 of thegas turbine engine 106. - As depicted in
FIG. 4 , theprobe receptacle 108 may include aninternal bore 118. Theinternal bore 118 may extend through thecap 116, themain body 112, and/or thecasing seal portion 114. Theinternal bore 118 may provide a passageway for theprobe 102 and theprobe attachment assembly 110 to move through theprobe receptacle 108. The size and shape of theinternal bore 118 may correspond to theprobe 102 and/or theprobe attachment assembly 110. - The
probe receptacle 108 may include abayonet slot 120. In some instances, thebayonet slot 120 may be disposed within thecap 116. Thebayonet slot 120 may include multiple portions that form a path along thecap 116. For example, as depicted inFIGS. 8 and 9 , thebayonet slot 120 may include afirst portion 122 extending from anopening 124 in a substantially axial direction relative to theprobe 102. At a bottom of thefirst portion 122, thebayonet slot 120 may include asecond portion 126 in the circumferential direction. Thebayonet slot 120 also may include athird portion 128, such as a notch, at and end of thesecond portion 126 that is oriented axially in the opposite direction of thefirst portion 122. For example, thebayonet slot 120 may be generally J-shaped. The length of thethird portion 128 may be equal to or less than a diameter of a bayonet. In other instances, thebayonet slot 120 may be generally L-shaped. Thebayonet slot 120 may be any shape. In some instances, thethird portion 128 may be omitted, and an external anti-rotation means may be used. For example, theprobe 102 may be secured on the outside of the casing to prevent rotation. - Referring back to
FIG. 4 , theprobe receptacle 108 may include aspring 130 disposed within theinternal bore 118 adjacent to thebayonet slot 120. In some instances, thespring 130 may be positioned within thecap 116. Abottom portion 132 of thespring 120 may abut anupper lip 134 of themain body 112. In some instances, awasher 136 may be disposed within theinternal bore 118 adjacent to thespring 130 and thebayonet slot 120. For example, thewasher 136 may be positioned on atop portion 138 of thespring 130. In some instances, the washer may be omitted. In some instances, thespring 130 may be omitted. As described below, the bellows seal 150 may act as a spring when compressed. In this manner, the bellows seal 150 may include enough spring stiffness to provided suitable resistance on thebayonet 146. - The
probe receptacle 108 may include a sealingsurface 140 within theinternal bore 118. In some instances, the sealingsurface 140 may be alip 142 within themain body 112. - As depicted in
FIGS. 5-7 , theprobe attachment assembly 110 may be disposed about theprobe 102. That is, the various components of theprobe attachment assembly 110 may be attached to theprobe 102. For example, theprobe attachment assembly 110 may be threaded onto theprobe 102. Theprobe attachment assembly 110 may be inserted into theprobe receptacle 108 via theinternal bore 118 and rotated to secure theprobe 102 in place. - The
probe attachment assembly 110 may include abushing 144 disposed about theprobe 102. Thebushing 144 may include at least onebayonet 146. Thebayonet 146 may be a protrusion or the like extending outward from thebushing 144. In some instances, the at least onebayonet 146 may include two bayonets spaced 180 degrees apart. Any number of bayonets may be used herein. Thebayonet 146 may be positioned within thebayonet slot 120. That is, for eachbayonet 146, there may be acorresponding bayonet slot 120. Thespring 130 may maintain thebayonet 146 within thebayonet slot 120. Moreover, thebayonet slot 120 may be shaped to provide tactile responses based on one or more locations of thebayonet 146 within thebayonet slot 120. For example, when thebayonet 146 enters thethird portion 128 of the bayonet slot 120 (i.e., the notch), an operator may feel a tactile response due to thespring 130 applying force on thebayonet 146 and forcing thebayonet 146 into the notch. Thespring 130 may maintain thebayonet 146 within the notch until a sufficient counter force is applied. - The
probe attachment assembly 110 also may include and aseal 148. Theseal 148 may be positioned adjacent to the sealingsurface 140 within theinternal bore 118. That is, theseal 148 may engage thelip 142 within themain body 112. In this manner, theseal 148 may form a seal at the sealingsurface 140 within theinternal bore 118. In some instances, the seal may be abellows seal 150. For example, the bellows seal 150 may be a corrugated sheet metal part that compresses under load forming a seal. Other types of seals may be used herein. As noted above, the bellows seal 150 may act as a spring to keep thebayonet 146 within theslot 120. - The
probe attachment assembly 110 further may include ahandle 152 for installing theprobe 102 into theprobe receptacle 108. Thehandle 152 may be attachable to theprobe 102. Thehandle 152 may be application specific. That is, the size and shape of thehandle 152 may vary. For example, thehandle 152 may be configured to pass through the outer casing of the gas turbine engine for attaching the probe to the inner casing of the gas turbine engine. Thehandle 152 may facilitate a user inserting and/or removing theprobe 102 from theprobe receptacle 108. Thehandle 152 also may facilitate an operator rotating theprobe 102 within theprobe receptacle 108. Moreover, thehandle 152 can be locked in place, thereby preventing rotation of theprobe 102, if, for example, thethird portion 128 of theslot 120 is omitted. Anti-rotation may prevent unintended disengagement of theprobe 102 from theprobe receptacle 108. - In use, the
probe 102 is inserted into theprobe receptacle 108 and rotated to lock it in place. During the insertion and rotation of theprobe 102, the bellows seal 150 may engage the sealingsurface 140 to prevent leakage around theprobe 102. Theprobe 102 may be removed by rotating it in the opposite direction and pulling it out. - As the
probe 102 is inserted into theprobe receptacle 108, an operator may rotate theprobe 102 until thebayonet 146 finds theopening 124 to thebayonet slot 120 so that thebayonet slot 120 may capture thebayonet 146. This operation can be done blindly, i.e., strictly by feel. Once thebayonet 146 is initially positioned in thebayonet slot 120, the operator may push down on theprobe 102 in the axial direction to overcome thespring 130 in theprobe receptacle 108. In some instances, the spring rate of thespring 130 may be high enough to prevent accidental (or unintended) disengagement but also low enough that the operator can overcome thespring 130 during installation and removal. - The operator may push down on the
probe 102 until thebayonet 146 bottoms out in thefirst portion 122 of thebayonet slot 120. The operator may then turn theprobe 102 until thebayonet 146 reaches the end of thesecond portion 126 of thebayonet slot 120. The operator may then remove pressure on theprobe handle 152, allowing thespring 130 to drive thebayonet 146 into the third portion 128 (i.e., the notch) of thebayonet slot 120. Once seated in the notch, thebayonet 146 is captured and theprobe 102 cannot move axially or circumferentially (unless an external force on theprobe 102 is sufficient to overcome the force applied by the spring 130). - During installation, when the operator pushes on the
probe 102 axially with thebayonet 146 in thefirst portion 122 of thebayonet slot 120, the bellows seal 150 makes contact with sealingsurface 140. As a result, the bellows seal 150 forms a seal about theprobe 102 within theprobe receptacle 108, preventing leakage of gas. Once thebayonet 146 is locked in the notch of thebayonet slot 120, the bellows seal 150 remains in contact with the sealingsurface 140. - When removing the
probe 102, the operator reverses the order of operations discussed above. It is noted that if theprobe receptacle 108 is threaded into acasing 104, the direction in which theprobe 102 is turned (clockwise or counterclockwise) is set such that the removal of theprobe 102 may tighten theprobe receptacle 108 into thecasing 104. This prevents accidental loosening of theprobe receptacle 108. - The
system 100 disclosed herein is generally referred to as a “quick connect/disconnect” system. In some instances, thesystem 100 enables theprobe 102 to be installed deep inside a cavity of thegas turbine engine 106 in which tools, such as wrenches or the like, cannot be used. In addition, thesystem 100 forms a seal about theprobe 102 during installation. Moreover, thesystem 100 enables an operator to install and/or remove theprobe 102 blindly. That is, installation and/or removal of theprobe 102 can be completed by feel. - In some instances,
gas turbine engines 106 may includemultiple casing 104. For example, somegas turbine engines 106 include an outer casing and an inner casing, which may be difficult to access due to space restrictions. Thesystem 100 disclosed herein enables the installation and/or removal of theprobe 102 in the inner casing. For example, thehandle 152 may pass through a small access port in the outer casing so that theprobe 102 may be inserted into and/or removed from theprobe receptacle 108 attached to the inner casing. - The
system 100 eliminates cross-threading and/or seizing of theprobe 102 in theprobe receptacle 108. Also, thesystem 100 provides a positive locking mechanism that prevents theprobe 102 from backing out. Further, thesystem 100 enables for precise positioning of theprobe 102 in the axially direction. Theprobe 102 can be quickly removed for inspection and reinstalled. - Although specific embodiments of the disclosure have been described, numerous other modifications and alternative embodiments are within the scope of the disclosure. For example, any of the functionality described with respect to a particular device or component may be performed by another device or component. Further, while specific device characteristics have been described, embodiments of the disclosure may relate to numerous other device characteristics. Further, although embodiments have been described in language specific to structural features and/or methodological acts, it is to be understood that the disclosure is not necessarily limited to the specific features or acts described. Rather, the specific features and acts are disclosed as illustrative forms of implementing the embodiments. Conditional language, such as, among others, “can,” “could,” “might,” or “may,” unless specifically stated otherwise, or otherwise understood within the context as used, is generally intended to convey that certain embodiments could include, while other embodiments may not include, certain features, elements, and/or steps. Thus, such conditional language is not generally intended to imply that features, elements, and/or steps are in any way required for one or more embodiments.
Claims (21)
1-20. (canceled)
21. A system for attaching a probe to a casing of a gas turbine engine, the system comprising:
a probe receptacle attached to the casing, wherein the probe receptacle comprises an internal bore and a bayonet slot; and
a probe attachment assembly configured to engage the probe receptacle, wherein the probe attachment assembly comprises a bayonet positionable within the bayonet slot.
22. The system of claim 21 , wherein the bayonet slot is substantially J-shaped.
23. The system of claim 21 , wherein the bayonet slot is shaped to provide a tactile response based on one or more locations of the bayonet within the bayonet slot.
24. The system of claim 21 , wherein the bayonet slot comprises:
a first portion extending from an opening;
a second portion extending from an end of the first portion; and
a third portion extending from an end of the second portion.
25. The system of claim 24 , wherein the third portion comprises a notch.
26. The system of claim 24 , further comprising a spring element disposed within the internal bore.
27. The system of claim 26 , wherein the spring element is configured to maintain the bayonet within the third portion of the bayonet slot.
28. The system of claim 24 , further comprising a spring element disposed about the probe.
29. The system of claim 28 , wherein the spring element is configured to maintain the bayonet within the third portion of the bayonet slot.
30. The system of claim 21 , further comprising:
a sealing surface within the internal bore; and
a seal positionable adjacent to the sealing surface.
31. The system of claim 21 , wherein the probe attachment assembly comprises a bushing.
32. The system of claim 21 , wherein the bayonet is attached to the bushing.
33. The system of claim 21 , further comprising a handle attachable to the probe attachment assembly for installing the probe into the probe receptacle.
34. A system for attaching one or more instruments to a casing of a gas turbine engine, the system comprising:
a probe;
a probe receptacle attached to the casing, wherein the probe receptacle comprises an internal bore and a bayonet slot; and
a probe attachment assembly configured to engage the probe receptacle, wherein the probe attachment assembly comprises a bayonet positionable within the bayonet slot.
35. The system of claim 34 , wherein the bayonet slot is substantially J-shaped.
36. The system of claim 34 , wherein the bayonet slot is shaped to provide a tactile response based on one or more locations of the bayonet within the bayonet slot.
37. The system of claim 34 , wherein the bayonet slot comprises:
a first portion extending from an opening;
a second portion extending from an end of the first portion; and
a third portion extending from an end of the second portion.
38. The system of claim 37 , wherein the third portion comprises a notch.
39. The system of claim 37 , further comprising a spring element disposed within the internal bore and/or about the probe.
40. A method for attaching a probe to a casing of a gas turbine engine, the method comprising:
attaching a probe receptacle to the casing, wherein the probe receptacle comprises an internal bore and a bayonet slot; and
removably attaching a probe attachment assembly configured to the probe receptacle, wherein the probe attachment assembly comprises a bayonet positionable within the bayonet slot.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US15/716,797 US20180017466A1 (en) | 2014-09-18 | 2017-09-27 | Systems and methods for attaching a probe to a casing of a gas turbine engine |
Applications Claiming Priority (2)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US14/489,759 US9778144B2 (en) | 2014-09-18 | 2014-09-18 | Systems and methods for attaching a probe to a casing of a gas turbine engine |
US15/716,797 US20180017466A1 (en) | 2014-09-18 | 2017-09-27 | Systems and methods for attaching a probe to a casing of a gas turbine engine |
Related Parent Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
US14/489,759 Continuation US9778144B2 (en) | 2014-09-18 | 2014-09-18 | Systems and methods for attaching a probe to a casing of a gas turbine engine |
Publications (1)
Publication Number | Publication Date |
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US20180017466A1 true US20180017466A1 (en) | 2018-01-18 |
Family
ID=55525518
Family Applications (2)
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US14/489,759 Active 2036-01-17 US9778144B2 (en) | 2014-09-18 | 2014-09-18 | Systems and methods for attaching a probe to a casing of a gas turbine engine |
US15/716,797 Abandoned US20180017466A1 (en) | 2014-09-18 | 2017-09-27 | Systems and methods for attaching a probe to a casing of a gas turbine engine |
Family Applications Before (1)
Application Number | Title | Priority Date | Filing Date |
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US14/489,759 Active 2036-01-17 US9778144B2 (en) | 2014-09-18 | 2014-09-18 | Systems and methods for attaching a probe to a casing of a gas turbine engine |
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US (2) | US9778144B2 (en) |
Families Citing this family (6)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US10107710B2 (en) * | 2016-09-22 | 2018-10-23 | Itron, Inc. | Mounting device for acoustic leak detection sensors |
CN107024354B (en) * | 2017-03-28 | 2019-05-17 | 北京航空航天大学 | A kind of probe mounting device suitable for Thin-Wall Outer Casing |
US11339830B2 (en) * | 2017-12-19 | 2022-05-24 | Itt Manufacturing Enterprises Llc | Bearing housing filler plate |
FR3111704B1 (en) * | 2020-06-19 | 2023-01-06 | Safran Aircraft Engines | DEVICE FOR MEASURING A PHYSICAL PARAMETER IN A TEST BENCH OF AN AIRCRAFT TURBOMACHINE, AND ASSOCIATED TEST BENCH |
US20220090513A1 (en) * | 2020-09-18 | 2022-03-24 | Ge Avio S.R.L. | Probe placement within a duct of a gas turbine engine |
US11821811B2 (en) * | 2022-02-04 | 2023-11-21 | Pratt & Whitney Canada Corp. | Fluid measurement system for an aircraft gas turbine engine and method for operating same |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
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US3751305A (en) * | 1971-03-10 | 1973-08-07 | Alco Standard Corp | Adjustable spring-loaded temperature sensing device |
US3936217A (en) * | 1975-01-31 | 1976-02-03 | Westinghouse Electric Corporation | Inspection port for turbines |
US4018083A (en) | 1975-08-22 | 1977-04-19 | General Electric Company | Vibration detection probe holder |
US4495810A (en) | 1983-04-20 | 1985-01-29 | General Electric Company | Probe mounting system |
US4614443A (en) * | 1984-11-29 | 1986-09-30 | Societe De Dietrich & Cie | Thermal sensor for chemical reactor |
GB8705905D0 (en) | 1987-03-12 | 1987-04-15 | Lucas Ind Plc | Combustion monitoring |
US4907456A (en) | 1988-03-24 | 1990-03-13 | Westinghouse Electric Corp. | Sensor probe system |
US5115636A (en) * | 1990-09-12 | 1992-05-26 | General Electric Company | Borescope plug |
US5185996A (en) * | 1990-12-21 | 1993-02-16 | Allied-Signal Inc. | Gas turbine engine sensor probe |
US5349850A (en) | 1992-11-19 | 1994-09-27 | General Electric Company | Instrumentation light probe holder |
DE19508916A1 (en) * | 1995-03-11 | 1996-09-12 | Abb Management Ag | High temperature probe |
US8039729B2 (en) * | 2005-03-30 | 2011-10-18 | Robertshaw Controls Company | Quick connect thermocouple mounting device and associated method of use |
DE102006061644B3 (en) * | 2006-12-27 | 2008-01-31 | Siemens Ag | Pulse generator has sealing device, where cylinder shaped generator has thread for screwing-in into tapped hole of wall element at one end, and has plug-in connection for electrical contacting of sensor element at the other end |
US9512737B2 (en) * | 2013-11-04 | 2016-12-06 | Siemens Energy, Inc. | Standardized gas turbine inspection port system |
-
2014
- 2014-09-18 US US14/489,759 patent/US9778144B2/en active Active
-
2017
- 2017-09-27 US US15/716,797 patent/US20180017466A1/en not_active Abandoned
Also Published As
Publication number | Publication date |
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US20160084736A1 (en) | 2016-03-24 |
US9778144B2 (en) | 2017-10-03 |
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