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. It also aims a means that should not require removal of the engine.
• 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 2946267 relating to wear indicators provided on the blades of the wheel of a compressor or on the wheel. -even
• a turbomachine comprising a housing with an internal wall delimiting a vein of fluid and the casing having at least one opening, opening into said vein and forming a passage for a endoscope, the opening, during operation of the turbomachine, being closed by a plug 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 near the plug.
• the invention it is possible, simply and without necessarily the implementation of any apparatus, to monitor 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.
• 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.
• FIG. 1 represents a bi-centrifugal gas turbine engine to which the invention applies;
• Figure 2 shows a detail of the engine of Figure 1, in perspective and cut tangentially along the axis thereof, at the elbow of the air flow downstream of the first diffuser, showing the endoscopy plug;
• FIG. 3 is a perspective view cut tangentially along the axis of the engine and seen from the inside, the detail of the endoscopy plug in position on the housing with a countersink forming the erosion witness of the first embodiment of the invention. invention;
• FIG. 4 shows the detail of the compressor of the motor of FIG. 1, in section at the level of the endoscopy plug, with a wear indicator according to the second embodiment of the invention
• Figure 5 shows the detail of Figure 4 without the cap
• Figure 6 shows a gas turbine engine with an axial and centrifugal compressor, to which the invention also applies.
• 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 shows in section a portion of the housing 7 of the engine of Figure 1, we see the elbow 3c of the air stream, 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 in Figure 2.
• the cap comprises a 8f that fits into the opening 7r so as to fill and prevent air leakage in 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 has an end surface portion 8s in accordance with the inner wall 3i so as to ensure continuity.
• a wear indicator is provided on the plug. It advantageously consists of a countersink 81 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 in FIG. 3.
• the depth of the countersink corresponds to the erosion potential of the internal 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 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 shows a gas turbine engine 10 with an axial and centrifugal compressor 12; 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)

Priority Applications (8)

Applications Claiming Priority (2)

Publications (1)

Family

ID=49753251

Family Applications (1)

Country Status (11)

Families Citing this family (2)

Citations (8)

Family Cites Families (7)

• 2013
  • 2013-05-21 FR FR1354556A patent/FR3006013B1/fr active Active
• 2014
  • 2014-05-13 PL PL14729423T patent/PL2999859T3/pl unknown
  • 2014-05-13 JP JP2016514457A patent/JP6411470B2/ja not_active Expired - Fee Related
  • 2014-05-13 US US14/891,641 patent/US10156155B2/en active Active
  • 2014-05-13 EP EP14729423.5A patent/EP2999859B1/fr active Active
  • 2014-05-13 CA CA2911875A patent/CA2911875C/fr active Active
  • 2014-05-13 ES ES14729423.5T patent/ES2616886T3/es active Active
  • 2014-05-13 CN CN201480028937.8A patent/CN105229266B/zh active Active
  • 2014-05-13 KR KR1020157033855A patent/KR102219495B1/ko not_active Expired - Fee Related
  • 2014-05-13 RU RU2015151391A patent/RU2657391C2/ru active
  • 2014-05-13 WO PCT/FR2014/051113 patent/WO2014188107A1/fr not_active Ceased

Patent Citations (8)

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