EP1524413A2 - Manchon de palier en électro-graphite pour une aube variable - Google Patents

Manchon de palier en électro-graphite pour une aube variable Download PDF

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Publication number
EP1524413A2
EP1524413A2 EP20040256376 EP04256376A EP1524413A2 EP 1524413 A2 EP1524413 A2 EP 1524413A2 EP 20040256376 EP20040256376 EP 20040256376 EP 04256376 A EP04256376 A EP 04256376A EP 1524413 A2 EP1524413 A2 EP 1524413A2
Authority
EP
European Patent Office
Prior art keywords
bushing
electro
graphitic carbon
liner
sleeve
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.)
Withdrawn
Application number
EP20040256376
Other languages
German (de)
English (en)
Inventor
Robert T. Brooks
Stuart A. Anderson
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
RTX Corp
Original Assignee
United Technologies Corp
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Publication of EP1524413A2 publication Critical patent/EP1524413A2/fr
Withdrawn legal-status Critical Current

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Classifications

    • 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
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • the present invention relates to an electro-graphitic bushing liner for reducing wear in gas turbine trunnions and bushings and a method for producing same.
  • variable vanes of the high compressor are held at the outer diameter by a trunnion bushing.
  • FIG. 1 there is illustrated the construction of a portion of an engine including the bushing 23.
  • the bushing 23 is situated between trunnion 15 and compressor outer case 22.
  • a variable vane 17 is attached to trunnion 15 via platform 21.
  • On either side of variable vane 17 is a blade 19.
  • Sync ring 13 is attached in such a manner as to enable a rotation of trunnion 15. As a result, the rotation of sync ring 13 provides the synchronized rotation of all variable vanes 17 per Stage.
  • bushing 23 is pressed into the compressor outer case 22 and is typically lined around its internal surface with a wear resistant and low friction material forming bushing lining 24.
  • bushing lining 24 is a fabric liner (0.018 inches (0.46 mm) thick impregnated with polyimide resin braded carbon fiber) which is bonded into the inner diameter of the bushing 23.
  • a bushing lining 24 constructed of polyimide resin braded carbon fiber is not capable of withstanding the high temperatures and loads of advanced high performance compressors.
  • bushings 23, to which such a fabric liner has been bonded are limited to 650°F to 700°F (343°C to 389°C) peak excursions as extended periods of exposure tend to rapidly degrade the liner resulting in metal to metal contact between the trunnion 15 and the bushing 23.
  • metal to metal contact serves to wear away the trunnion 15 and the bushing 23 so as to alter the physical geometry of both.
  • the tightness of the fit between the bushing 23 and the compressor outer case 22 is similarly altered.
  • Such an alteration in the geometry ultimately results in an angular displacement of a variable vane 17.
  • Such displacement of variable vane 17 can be catastrophic.
  • variable vane 17 if a variable vane 17 is displaced with respect to adjacent vanes by more than 6°, a catastrophic surge may be induced. It is therefore of the utmost importance that the trunnion 15 and bushing 23 operate in such a manner as to maintain their shapes and, thus, maintain a constant variable vane 17 angle.
  • an object of the present invention to provide an electro-graphitic bushing liner for reducing wear in gas turbine trunnions and bushings and a method for producing same.
  • a method for improving the wear characteristics of bushings comprises the steps of providing a bushing comprising an internal surface having an inner diameter and opposing ends, and pressing a graphite based substance around the internal surface of the bushing.
  • a wear resistant bushing comprises a bushing comprising an internal surface having an inner diameter and opposing ends, and a graphite based liner/sleeve pressed around the internal surface of the bushing.
  • a bushing assembly comprises a bushing comprising an internal surface having an inner diameter and opposing ends, a trunnion, and a graphite based liner/sleeve pressed around the internal surface of the bushing in contact with the trunnion and the bushing.
  • a bushing 23 into which is press fitted a sleeve composed of a graphite based substance, preferably electro-graphitic carbon.
  • a sleeve composed of a graphite based substance, preferably electro-graphitic carbon.
  • the prior art made use of a polyimide resin braded carbon fiber which was bonded to the inner diameter of the bushing 23
  • the electro-graphitic carbon liner/sleeve 11 of the present invention is press fitted about an inner diameter of a bushing 23 of the present invention.
  • the electro-graphitic carbon liner sleeve of the present invention does not suffer significant breakdown even at temperatures approximating 1050°F (566°C).
  • the electro-graphitic carbon liner/sleeve of the present invention both self lubricates as well as maintains the appropriate distance between the inner diameter of the bushing 23 and the trunnion 15.
  • the bushing of the present invention may operate for extended periods of time at high temperatures while maintaining its geometry so as to avoid unwanted deflection of the variable vane.
  • an electro-graphitic carbon rod 51 having a diameter equal to the bushing inner diameter 53 is inserted into the interior of bushing 23 such that opposing ends of the electro-graphitic carbon rod 51 extend beyond normal lines 35.
  • Normal lines 35 extend at a right angle from the sides of bushing 23 at opposing ends of bushing 23.
  • electro-graphitic carbon rod 51 is drilled along bushing centerline 31 to form a hole having a drill hole diameter 41.
  • the hole is further reamed to form a hole extending along bushing centerline 31 having a diameter equal to ream hole diameter 43.
  • the difference between ream hole diameter 43 and the bushing inner diameter 53 is equivalent to the thickness of the electro-graphitic carbon liner sleeve which is thus formed pressing against the inner diameter of bushing 23.
  • the electro-graphitic carbon liner sleeve 11 With the electro-graphitic carbon liner sleeve 11 thusly formed, it is preferable to chamfer or otherwise machine the electro-graphitic carbon liner sleeve 11. Were one to allow electro-graphitic carbon liner sleeve 11 to extend at either end parallel to normal line 35, the result would be an increase in the probability of damage to the electro-graphitic carbon liner/sleeve 11. In operation, the stresses transmitted to the trunnion 15 and bushing 23 from the variable vane 17 can be substantial. These forces serve to encourage the trunnion 15 and bushing 23 to rock in a pendulum-like motion away from being parallel to bushing centerline 31.
  • the angle ⁇ between the chamfered surface 55 of electro-graphitic carbon liner sleeve 11 extending at an angle ⁇ from normal line 35 is between 5 and 85°. Most preferably, the chamfer angle ⁇ is approximately 45°.
  • the present invention is not so limited. Rather, the present invention is drawn broadly to encompass any and all shapes to which chamfer surface 55 might be machined including but not limited to curves.
  • the bushing is fabricated from a titanium based alloy.
  • the bushing 23 of the present invention fitted with the electro-graphitic carbon liner sleeve 11 has been seen to experience no wear of the trunnion after durations of operation in excess of forty hours. It was observed that, as the trunnion rotated and moved with respect to the bushing 23, and subsequently wore upon the electro-graphitic carbon liner/sleeve 11, the electro-graphitic carbon liner sleeve 11 adhered to and filled voids created in the outer surface of the trunnion 15. In this manner, the electro-graphitic carbon liner/sleeve 11 was self lubricating and acted to provide a very stable lubricious graphite-to-graphite contact surface.
  • FIGS. 4a and 4b there is graphically illustrated the incidence of wear occurring over time with the bushing lining known in the art.
  • FIG. 4a makes evident, after four hours of operation at 750°F (399°C), both the inner diameter and outer diameter side of the bushing lining exhibited wear between approximately .008 inches (0.2 mm) and .014 inches (0.36 mm).
  • FIG. 4b makes evident, the wear on the trunnion after four hours of operation is approximately .005 inches (0.13 mm).
  • FIGS. 5a and 5b there is graphically illustrated the wear experienced when using an electro-graphitic carbon liner/sleeve 11 of the present invention.
  • the electro-graphitic carbon liner/sleeve 11 experiences an inner diameter and outer diameter wear after 40 hours of approximately .004 inches (0.1 mm).
  • FIG. 5b makes clear, after 40 hours, the trunnion exhibits no wear. As noted above, this is the result of graphite being detached from the electro-graphitic carbon liner sleeve and redepositing upon the trunnion so as to protect the trunnion.
  • the electro-graphitic carbon liner sleeve 11 of the present invention does exhibit wear, the amount of material worn off is redeposited elsewhere on the trunnion and bushing and does not alter the geometry of the fit between the parts. Therefore, while the electro-graphitic carbon liner sleeve 11 does exhibit wear, the trunnion exhibits no discernible wear at all.
  • the electro-graphitic carbon liner sleeve of the present invention is pressed rather than bonded to the metal bushing, it can be pressed out and replaced with a brand new liner.
  • the resultant repaired bushing can be reused for the full life of the engine and is approximately 25% the cost of a new bushing.
  • the electro-graphitic carbon liner sleeve 11 of the present invention can be machined with very tight tolerances.
  • the current method of bonding a bushing lining as known in the art makes use of a bonded fabric that has less controllable tolerances than a graphite liner of the present invention.
  • a result of the improved tolerance control of the present invention is less wear and improved variable vane position accuracy.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Control Of Turbines (AREA)
EP20040256376 2003-10-15 2004-10-15 Manchon de palier en électro-graphite pour une aube variable Withdrawn EP1524413A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US685611 1991-04-15
US68561103A 2003-10-15 2003-10-15

Publications (1)

Publication Number Publication Date
EP1524413A2 true EP1524413A2 (fr) 2005-04-20

Family

ID=34377623

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20040256376 Withdrawn EP1524413A2 (fr) 2003-10-15 2004-10-15 Manchon de palier en électro-graphite pour une aube variable

Country Status (2)

Country Link
EP (1) EP1524413A2 (fr)
JP (1) JP2005171986A (fr)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1741984A2 (fr) 2005-06-30 2007-01-10 United Technologies Corporation Traversée de conduit de système de post-combustion
EP1803902A1 (fr) 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Dispositif de support pour un anneau de réglage enveloppant un support d'aubes circulaire espacé
EP1803903A1 (fr) 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Dispositif de rotation pour pales réglables d'une turbine
EP1806480A1 (fr) * 2006-01-06 2007-07-11 Snecma Dispositif anti-usure pour pivot de guidage d'aube à angle de calage variable de compresseur de turbomachine
US7722318B2 (en) 2007-02-13 2010-05-25 United Technologies Corporation Hole liners for repair of vane counterbore holes
WO2011101334A1 (fr) 2010-02-19 2011-08-25 Siemens Aktiengesellschaft Dispositif d'entraînement destiné à faire pivoter les aubes réglables d'une turbomachine
EP2362071A1 (fr) 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine
EP1980721A3 (fr) * 2007-04-10 2011-10-05 United Technologies Corporation Ensemble d'aube de stator orientable pour moteur de turbine
US8794910B2 (en) 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US8864450B2 (en) 2011-02-01 2014-10-21 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US9863468B2 (en) 2013-09-17 2018-01-09 Sikorsky Aircraft Corporation Rod end wear prevention
US11346235B2 (en) * 2019-06-04 2022-05-31 Raytheon Technologies Corporation Bushing for variable vane in a gas turbine engine
RU2781457C1 (ru) * 2021-12-24 2022-10-12 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Устройство управления направляющими аппаратами компрессора газотурбинного двигателя

Cited By (24)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1741984A3 (fr) * 2005-06-30 2009-10-21 United Technologies Corporation Traversée de conduit de système de post-combustion
EP1741984A2 (fr) 2005-06-30 2007-01-10 United Technologies Corporation Traversée de conduit de système de post-combustion
EP1803902A1 (fr) 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Dispositif de support pour un anneau de réglage enveloppant un support d'aubes circulaire espacé
EP1803903A1 (fr) 2006-01-02 2007-07-04 Siemens Aktiengesellschaft Dispositif de rotation pour pales réglables d'une turbine
US7828516B2 (en) 2006-01-02 2010-11-09 Siemens Aktiengesellschaft Device for support of an adjusting ring which encompasses at a distance a circular blade carrier
CN1995763B (zh) * 2006-01-06 2011-01-12 斯奈克玛 变斜度叶片及具有该叶片的涡轮机和其压缩机
EP1806480A1 (fr) * 2006-01-06 2007-07-11 Snecma Dispositif anti-usure pour pivot de guidage d'aube à angle de calage variable de compresseur de turbomachine
FR2896012A1 (fr) * 2006-01-06 2007-07-13 Snecma Sa Dispositif anti-usure pour pivot de guidage d'aube a angle de calage variable de compresseur de turbomachine
RU2420662C2 (ru) * 2006-01-06 2011-06-10 Снекма Противоизносное устройство для направляющего валика лопатки с изменяемым углом установки в компрессоре газотурбинного двигателя, компрессор газотурбинного двигателя и газотурбинный двигатель
EP2565380A3 (fr) * 2007-02-13 2016-10-05 United Technologies Corporation Manchons pour la réparation de trous de virole de contre-alésage d'aubes à calage variable
US7722318B2 (en) 2007-02-13 2010-05-25 United Technologies Corporation Hole liners for repair of vane counterbore holes
EP1959094A3 (fr) * 2007-02-13 2010-06-16 United Technologies Corporation Rustines pour la réparation de trous de contre-alésage d'aube
US9353643B2 (en) 2007-04-10 2016-05-31 United Technologies Corporation Variable stator vane assembly for a turbine engine
EP1980721A3 (fr) * 2007-04-10 2011-10-05 United Technologies Corporation Ensemble d'aube de stator orientable pour moteur de turbine
WO2011101334A1 (fr) 2010-02-19 2011-08-25 Siemens Aktiengesellschaft Dispositif d'entraînement destiné à faire pivoter les aubes réglables d'une turbomachine
EP2362070A1 (fr) 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine
EP2362071A1 (fr) 2010-02-19 2011-08-31 Siemens Aktiengesellschaft Dispositif d'entraînement pour le pivotement d'aubes réglables d'une turbomachine
US8864450B2 (en) 2011-02-01 2014-10-21 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US8794910B2 (en) 2011-02-01 2014-08-05 United Technologies Corporation Gas turbine engine synchronizing ring bumper
US9863468B2 (en) 2013-09-17 2018-01-09 Sikorsky Aircraft Corporation Rod end wear prevention
US11346235B2 (en) * 2019-06-04 2022-05-31 Raytheon Technologies Corporation Bushing for variable vane in a gas turbine engine
US20220282629A1 (en) * 2019-06-04 2022-09-08 Raytheon Technologies Corporation Bushing for variable vane in a gas turbine engine
US11746665B2 (en) 2019-06-04 2023-09-05 Rtx Corporation Bushing for variable vane in a gas turbine engine
RU2781457C1 (ru) * 2021-12-24 2022-10-12 Публичное акционерное общество "ОДК-Уфимское моторостроительное производственное объединение" (ПАО "ОДК-УМПО") Устройство управления направляющими аппаратами компрессора газотурбинного двигателя

Also Published As

Publication number Publication date
JP2005171986A (ja) 2005-06-30

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