EP2999859B1 - Turbomachine comportant un temoin d'usure du carter - Google Patents

Turbomachine comportant un temoin d'usure du carter Download PDF

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Publication number
EP2999859B1
EP2999859B1 EP14729423.5A EP14729423A EP2999859B1 EP 2999859 B1 EP2999859 B1 EP 2999859B1 EP 14729423 A EP14729423 A EP 14729423A EP 2999859 B1 EP2999859 B1 EP 2999859B1
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EP
European Patent Office
Prior art keywords
opening
wall
turbine engine
casing
wear indicator
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.)
Active
Application number
EP14729423.5A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP2999859A1 (fr
Inventor
Sylvain Jacques Marie GOURDANT
Laurent Jacquet
Philippe NECTOUTE
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.)
Safran Helicopter Engines SAS
Original Assignee
Safran Helicopter Engines SAS
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Publication date
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Priority to PL14729423T priority Critical patent/PL2999859T3/pl
Publication of EP2999859A1 publication Critical patent/EP2999859A1/fr
Application granted granted Critical
Publication of EP2999859B1 publication Critical patent/EP2999859B1/fr
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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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/14—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for responsive to other specific conditions
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F01D21/003—Arrangements for testing or measuring
    • 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
    • F01D21/00—Shutting-down of machines or engines, e.g. in emergency; Regulating, controlling, or safety means not otherwise provided for
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/4206—Casings; Connections of working fluid for radial or helico-centrifugal pumps especially adapted for elastic fluid pumps
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/329—Application in turbines in gas turbines in helicopters
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2260/00—Function
    • F05D2260/80—Diagnostics

Definitions

  • the present invention relates to the field of turbomachines, more particularly that of gas turbine engine compressors, in particular centrifugal compressors.
  • the invention provides a means for detecting, in a simple manner, the state of wear of certain parts of the turbomachine.
  • the gas turbine engines used for driving the rotor blades of a helicopter consist of radial or axial flow air veins for part of the trajectory.
  • a known motor comprises a first rotor consisting of a set of two centrifugal compressors in series - this assembly is driven by an axial turbine - and a second free turbine rotor, downstream of the turbine of the first rotor, for the driving a power shaft.
  • Another example of a known motor comprises a first rotor formed of an assembly of a three-stage axial compressor and a centrifugal compressor, arranged in series and driven by two axial turbines; a second rotor is formed of a twin turbine receiving the gases of the turbine of the first rotor and driving a power shaft.
  • the object of the invention is a means for detecting and quantifying the erosion caused by the ingestion of particles in the air stream.
  • the invention relates more particularly to certain areas of the air stream that are not subject to strong erosion and for which simplified monitoring would be desirable.
  • This is for example the inner wall of the bend downstream of the diffuser of the coating of abradable material or the housing without such a coating, vis-à-vis the tops of the blades of the axial rotor.
  • the cover of the compressor wheel which is covered on its inner face with an abradable coating comprises in a substantially middle part thereof, machined markers in the form of countersink and given depths in the abradable material.
  • Wear monitoring is performed by endoscopic examinations. An endoscope is introduced into the compressor and an active end of the endoscope is positioned opposite the markings to provide an image signal of the markings. The endoscopic signal is a function of the number of markers and the wear in their place; it is treated to provide a motor removal decision criterion for changing and repairing worn parts.
  • Concerning this problem of wear indicator other patent applications have been filed, such as FR 2938651 or FR 2942267 relating to wear indicators provided on the blades of the wheel of a compressor or on the wheel itself
  • a turbomachine comprising a casing with an inner wall delimiting a stream of air and the casing having at least one opening, opening into said vein and forming a passage for a endoscope, the opening, during the operation of the turbomachine, being closed by a cap having an end surface portion ensuring the continuity of the inner wall of the housing, is characterized in that a wear indicator of the internal wall of the housing is associated with the plug or the inner wall of the housing, at the edge of the opening or opening into the opening.
  • the invention it is possible, simply and without necessarily the implementation of any apparatus, to monitor the wear in areas of the turbomachine that are not directly accessible and that previously required disassembly operations and removing the engine. Depending on the state of the wear indicator, it is easy to decide whether to disassemble the turbomachine to perform the repair.
  • the wear indicator is in the form of a countersink machined in said end surface portion of the plug.
  • This embodiment is suitable when said surface portion of the plug is flush with the inner wall of the housing.
  • the plug is made of the same material as this one.
  • the wear indicator is a notch machined in the inner wall of the housing and which is visible from the outside through said opening forming an endoscope passage. According to this embodiment the plug may not be flush with the air stream.
  • the depth of the counterbore is preferably chosen to correspond to the internal wall thickness that can be removed by erosion in the event of acceptable erosion of the zone. In this way, when the countersink is no longer visible, it is time to repair the part.
  • the invention aims in particular a centrifugal compressor whose opening, forming a passage for an endoscope, with wear indicator is located in the downstream bend of the diffuser, at the output of a compressor stage.
  • the invention also relates to an axial compressor or the axial part of a compressor, the opening forming a passage for an endoscope is located near an abradable coating vis-à-vis the tops of the rotor blades of the compressor.
  • a gas turbine engine 1 known per se for driving the blades of a helicopter rotor. It comprises a gas generator part with a bi-centrifugal compressor that is to say with two compression wheels 2 and 4 respectively integral with a coaxial turbine 6.
  • the air stream 3 inside the housing is annular and extends from an air inlet 3a which guides the air to the axial inlet of the compressor 2.
  • the compressed air by the compressor is guided radially through the diffuser 3b.
  • the air stream then forms a bend 3c so as to bring the air towards the axis of the machine to the axial inlet of the second compression wheel 4.
  • the air is then guided to the chamber of combustion 5 which supplies the turbine 6 with hot gas.
  • the expansion of the gases continues in the turbine 9 of a second rotor secured to a power take-off shaft for driving the load.
  • the air stream is delimited by two coaxial walls whose inner wall 3i of the casing 7.
  • FIG 2 which represents in section a portion of the casing 7 of the engine of the figure 1 we see the elbow 3c of the air vein, downstream of the diffuser 3b.
  • This elbow serves to deflect the air flow from the diffuser to the axis of the machine.
  • a radial opening 7r is arranged in the casing 7 at the elbow 3c. This opening opens into the vein of air and allows the passage of an unrepresented endoscope by which an inspection of the interior of the air vein can be performed.
  • This opening 7r is normally closed by a plug 8 which is seen in section on the figure 2 .
  • the plug comprises a 8f that fits into the opening 7r so as to fill it and prevent air leakage during operation of the machine; it is secured to a transverse locking plate 8v through which the cap is bolted to the casing 7.
  • the plug 8 On the opposite side, the plug 8 has an end surface portion 8s conforming to the inner wall 3i so as to to ensure continuity.
  • a wear indicator is provided on the plug. It advantageously consists of a countersink 8l machined on the surface portion 8s of the plug.
  • the shape of the counterbore can be circular, oval or any other profile.
  • This countersink 81 is visible on the figure 3 .
  • the depth of the counterbore corresponds to the erosion potential of the inner wall 3i. It is thus very easy to check the state of wear of the part. If the countersink is no longer visible when removing the plug 8, it means that the erosion potential is consumed. The part is then to be repaired or replaced.
  • the end surface portion 8s of the plug is slightly set back relative to the inner wall 3i.
  • Practicing the erosion witness in the form of a notch 3s in the inner wall on the edge of the opening 7r makes it possible not to be hindered by such withdrawal from the end of the plug.
  • This notch 3s opening into the opening 7r is visible from outside the housing when the cap has been removed.
  • This situation is represented on the figure 5 .
  • the depth of the notch in the inner wall 3i corresponds to the erosion potential thereof. If the notch 3s is no longer visible to the naked eye or the endoscope, it means that the potential for internal wall erosion is consumed. A repair is indicated.
  • the erosion of the inner wall does not occur symmetrically around the axis of the machine, it depends on the position of the engine on the aircraft or the shape of the air inlet. It is then appropriate to provide an opening for the passage of the endoscope in the area likely to be most affected by erosion. It must also take into account the accessibility of the opening for the endoscope.
  • FIG. 6 there is shown a gas turbine engine 10 with a compressor 12, axial and centrifugal; the first stages 121 of the compressor are axial.
  • the housing 17 enveloping the first stages 121 has an opening for the passage of an endoscope, the present invention is advantageously applied to the monitoring of erosion of the inner wall of the housing in this area.
  • the solution is not illustrated in the figure but is easily deduced from the solution described for the inner wall of the housing in the area of the downstream elbow of a centrifugal compressor.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)
EP14729423.5A 2013-05-21 2014-05-13 Turbomachine comportant un temoin d'usure du carter Active EP2999859B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
PL14729423T PL2999859T3 (pl) 2013-05-21 2014-05-13 Maszyna wirowa zawierająca wskaźnik zużycia obudowy

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1354556A FR3006013B1 (fr) 2013-05-21 2013-05-21 Turbomachine comportant un temoin d'usure du carter
PCT/FR2014/051113 WO2014188107A1 (fr) 2013-05-21 2014-05-13 Turbomachine comportant un temoin d'usure du carter

Publications (2)

Publication Number Publication Date
EP2999859A1 EP2999859A1 (fr) 2016-03-30
EP2999859B1 true EP2999859B1 (fr) 2017-01-25

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP14729423.5A Active EP2999859B1 (fr) 2013-05-21 2014-05-13 Turbomachine comportant un temoin d'usure du carter

Country Status (11)

Country Link
US (1) US10156155B2 (enExample)
EP (1) EP2999859B1 (enExample)
JP (1) JP6411470B2 (enExample)
KR (1) KR102219495B1 (enExample)
CN (1) CN105229266B (enExample)
CA (1) CA2911875C (enExample)
ES (1) ES2616886T3 (enExample)
FR (1) FR3006013B1 (enExample)
PL (1) PL2999859T3 (enExample)
RU (1) RU2657391C2 (enExample)
WO (1) WO2014188107A1 (enExample)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB201415201D0 (en) * 2014-08-28 2014-10-15 Rolls Royce Plc A wear monitor for a gas turbine engine fan
GB202115178D0 (en) 2021-10-22 2021-12-08 Rolls Royce Plc Gas passage

Family Cites Families (15)

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Publication number Priority date Publication date Assignee Title
FR1159071A (fr) 1955-10-21 1958-06-23 Borg Warner Dispositif de commande automatique de programmes d'opérations
US3936217A (en) * 1975-01-31 1976-02-03 Westinghouse Electric Corporation Inspection port for turbines
SU567847A1 (ru) * 1976-04-12 1977-08-05 Всесоюзный научно-исследовательский институт природных газов Центробежный компрессор
US4406580A (en) * 1981-07-23 1983-09-27 United Technologies Corporation Inspection hole plug for gas turbine engine
SU1408119A1 (ru) * 1986-04-07 1988-07-07 Всесоюзный научно-исследовательский и конструкторско-технологический институт компрессорного машиностроения Сигнализатор износа элементов проточной части компрессора
US5472315A (en) * 1993-11-09 1995-12-05 Sundstrand Corporation Abradable coating in a gas turbine engine
US7967554B2 (en) * 2007-06-18 2011-06-28 Honeywell International Inc. Turbine cooling air centrifugal particle separator
FR2938651B1 (fr) * 2008-11-14 2011-03-04 Turbomeca Procede et ensemble de determination de l'usure du bord d'attaque d'une pale
FR2942267B1 (fr) * 2009-02-19 2011-05-06 Turbomeca Temoin d'erosion pour roue de compresseur
FR2946267B1 (fr) 2009-06-05 2012-06-29 Centre Nat Rech Scient Procede de preparation d'une composition organocompatible et hydrocompatible de nanocristaux metalliques et composition obtenue
US8684669B2 (en) * 2011-02-15 2014-04-01 Siemens Energy, Inc. Turbine tip clearance measurement
FR2973003B1 (fr) * 2011-03-21 2013-03-29 Jpb Systeme Dispositif d'obturation a verrouillage auto-activable
US9322280B2 (en) * 2011-08-12 2016-04-26 United Technologies Corporation Method of measuring turbine blade tip erosion
FR2981131B1 (fr) * 2011-10-07 2013-11-01 Turbomeca Compresseur centrifuge equipe d'un marqueur de mesure d'usure et procede de suivi d'usure utilisant ce marqueur
GB201216703D0 (en) * 2012-09-19 2012-10-31 Rolls Royce Plc A boroscope and a method of laser processing a component within an assembled apparatus using a boroscope

Non-Patent Citations (1)

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Title
None *

Also Published As

Publication number Publication date
ES2616886T3 (es) 2017-06-14
KR102219495B1 (ko) 2021-02-23
CN105229266A (zh) 2016-01-06
CA2911875A1 (fr) 2014-11-27
KR20160009578A (ko) 2016-01-26
CA2911875C (fr) 2021-02-23
PL2999859T3 (pl) 2017-07-31
EP2999859A1 (fr) 2016-03-30
CN105229266B (zh) 2017-12-12
RU2657391C2 (ru) 2018-06-13
WO2014188107A1 (fr) 2014-11-27
RU2015151391A (ru) 2017-06-26
JP2016519255A (ja) 2016-06-30
JP6411470B2 (ja) 2018-10-24
FR3006013A1 (fr) 2014-11-28
US10156155B2 (en) 2018-12-18
FR3006013B1 (fr) 2017-10-13
RU2015151391A3 (enExample) 2018-04-03
US20160084107A1 (en) 2016-03-24

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