EP1704933A1 - Verfahren zum Präparieren, Reinigen und Reparieren eines Artikels, sowie der reparierte Artikel - Google Patents

Verfahren zum Präparieren, Reinigen und Reparieren eines Artikels, sowie der reparierte Artikel Download PDF

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Publication number
EP1704933A1
EP1704933A1 EP05251713A EP05251713A EP1704933A1 EP 1704933 A1 EP1704933 A1 EP 1704933A1 EP 05251713 A EP05251713 A EP 05251713A EP 05251713 A EP05251713 A EP 05251713A EP 1704933 A1 EP1704933 A1 EP 1704933A1
Authority
EP
European Patent Office
Prior art keywords
cavity
foreign material
opening
additional opening
creating
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.)
Granted
Application number
EP05251713A
Other languages
English (en)
French (fr)
Other versions
EP1704933B1 (de
Inventor
John Shearer Succop
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.)
Raytheon Technologies Corp
Original Assignee
United Technologies Corp
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Filing date
Publication date
Application filed by United Technologies Corp filed Critical United Technologies Corp
Priority to EP05251713A priority Critical patent/EP1704933B1/de
Publication of EP1704933A1 publication Critical patent/EP1704933A1/de
Application granted granted Critical
Publication of EP1704933B1 publication Critical patent/EP1704933B1/de
Expired - Fee Related legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B08—CLEANING
    • B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
    • B08B9/00—Cleaning hollow articles by methods or apparatus specially adapted thereto 
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/002—Cleaning of turbomachines
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/32—Collecting of condensation water; Drainage ; Removing solid particles
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
    • F01D5/187—Convection cooling

Definitions

  • This invention relates to methods of preparing, cleaning and repairing an article and the repaired article.
  • a method of preparing a part for cleaning comprising the steps of: providing a part with an internal cavity, at least one opening in communication with the cavity, and foreign material within the cavity; and creating an additional opening in the part at a location adjacent the foreign material.
  • a method of cleaning a part comprising the steps of: providing a part with an internal cavity, at least one opening in communication with the cavity; creating an additional opening in the part; and flushing the cavity with a fluid.
  • the additional opening acts as an exit or entrance for the fluid.
  • a method of repairing a part comprising the steps of: providing a part with an internal cavity, at least one opening in communication with the cavity, and foreign material within the cavity; creating an additional opening in the part; and removing the foreign material.
  • the removing step occurs through the additional opening.
  • a part comprising: an exterior surface; an internal cavity; at least one opening through the surface and in communication with the cavity; and a repaired section of the surface.
  • the repaired section was an additional opening that provided a temporary exit or entrance to the cavity for removing foreign material from the cavity.
  • Figure 1 displays a gas turbine engine 10 used, for example, for propulsion or power generation.
  • the engine 10 includes a fan section 14, a compressor section 16, a burner section 18 and a turbine section 20.
  • the fan section 14 draws air 22 into the engine 10. A portion of the air 22 drawn in by the fan section 14 travels into the compressor 16 (i.e. "core engine flow"), while the remainder (i.e. "bypass flow”) does not.
  • the core engine flow becomes compressed traveling through the compressor section 16, then mixes with fuel supplied by fuel injectors in the burner section 18. Within the burner section 18, the air/fuel mixture combusts. The combustion gases exit the burner section 18 and enter the turbine section 20. The combustion gases drive the turbine section 18.
  • Figure 2 displays a portion of the turbine section 20. Specifically, the figure displays a turbine blade 22 with a root section 26 and an airfoil section 28 separated by a platform 30.
  • the root section 26 secures to a correspondingly shaped feature on a rotor 32 (shown in phantom). Since the platform 30, in combination with other features of the engine 10, defines the radially inner boundary of the core gas path, the airfoil section 28 resides within the core gas path.
  • the engine case 34 (shown in phantom) defines the radially outer boundary of the core gas path.
  • the engine 10 introduces cooling air to the turbine section 20.
  • the engine 10 draws such cooling air from the compressor section 16.
  • One path for introducing cooling air to the turbine section 20 is through the turbine blades 22.
  • the turbine blade 22 is hollow so as to receive cooling air CA.
  • FIG. 3 displays a cross-sectional view of the turbine blade 22.
  • the turbine blade 22 has an internal cavity 36.
  • the cavity 36 includes one or more openings, such as one or more inlets 38 and one or more outlets 40.
  • the turbine blade 22 could include one or more internal walls 44 arranged to form a serpentine passageway 46 between the inlets 38 and outlets 40.
  • the cooling air CA can enter the internal cavity 36 through the inlets 38, travel along the passageway 46, then exit the outlets 40.
  • the outlets 40 could reside anywhere on the airfoil section 28 and in any desired arrangement.
  • foreign material F can become trapped within the cavity 36.
  • Various causes can introduce the foreign material F to the cavity 36.
  • harsh operating conditions can introduce the foreign material F (e.g. sand) into the engine 10.
  • maintenance operations e.g. coating removal
  • the foreign material F can be introduced to the cavity 36.
  • the manufacturing process that produces the turbine blade 22 could introduce the foreign material F.
  • the foreign material F could reside at any location within the cavity 36.
  • the presence of the foreign material F within the cavity 36 can reduce the effectiveness of the cooling air CA. Unless successful removal of the foreign material F occurs, the turbine blade 22 will likely not return to service (i.e. scrapped). Scrapping a turbine blade 22 can be costly. Removal of the foreign material F from the cavity 36 can prove difficult for several reasons. First, the operation of the engine 22 with the foreign material F present, the performance of maintenance operations and the manufacturing processes tend to sinter the foreign material F in place. Second, the typical size of the inlets 38 and outlets 40 and the shape of the serpentine passageway 46 make access to the foreign material F difficult.
  • One step in a possible method of removing the foreign material F is to locate the foreign material F within the cavity 36.
  • various techniques are available to locate the foreign material. For example, the technician may visually identify the location of the foreign material F. Most likely, however, the technician would need to rely on suitable machines to locate the foreign material F. For instance, the technician could use x-ray, neutron radiography, ultrasound and thermal imaging to locate the foreign material F.
  • FIG. 5 shows the turbine blade 22 with an additional opening 48 in communication with the cavity 36.
  • the technician could rely on any suitable technique to create the additional opening 48 in the turbine blade 22.
  • a technician could utilize a router, milling machines, electrical discharge machining (EDM) or laser drilling to create the additional opening 48.
  • the additional opening 48 could have the shape of a channel on the tip of the turbine blade 22, transversing the turbine blade 22 from a concave side to a convex side of the airfoil section 28, but other shapes are possible.
  • the figure also shows the opening 48 extending in the radial direction, but other orientations (e.g. angled relative to the radial direction) are possible.
  • the additional opening 48 could have any suitable position on the turbine blade 22.
  • the position of the additional opening 48 could be selected relative to the location of the foreign material F and to the specific techniques used in later method steps.
  • one suitable location for the additional opening 48 is radially outboard of the foreign material F and as close to the foreign material F as possible.
  • the additional opening 48 is downstream of the foreign material F.
  • Performing the locating step is not mandatory. Without the locating step, the technician does not know the exact location of foreign material or if foreign material even resides within the cavity 36. In this instance, one suitable location for the additional opening 48 is adjacent an expected location of the foreign material F, determined either by prior experience or estimation. After adding the additional opening 48, preparation of the turbine blade 22 has occurred. The turbine blade 22 can proceed to another step in a possible method, the removal of the foreign material F.
  • Figure 6 shows another step in a possible method of removing the foreign material F.
  • the figure displays a cleaning device for the cavity 36, such as a highpressure washer 50.
  • the washer includes a fluid source 52, a manifold 54 for receiving fluid W from the fluid source 52 and one or more probes 56 for discharging the fluid into the cavity 36.
  • the shape of the serpentine passageway 46 can determine the length and positioning of the probes 56 within the cavity 36. As an example, the location of the probes 56 helps direct the fluid through the serpentine passageway 46 and out of the cavity 36. While water appears the most economical and environmentally friendly choice to flush out the foreign material F, the washer 50 could operate with other fluids, or even with water having additives therein.
  • the washer 50 could operate, for example, at pressures of between approximately 1000 and 20,000 psi (6.9 and 137.9 MPa). In addition, the washer 50 could have an automatic wash cycle or the technician could manually operate the washer 50. As an example, the washer 50 could be a HDP52 Power Flush unit available from Hammelmann Corporation of Dayton, Ohio.
  • the probes 56 could enter the cavity 36 through any suitable opening.
  • the probes 56 could enter the cavity 36 through the outlets 40 or the additional opening 48. That allows the additional opening 48 to either serve as an entrance for the fluid into the cavity 36 or, as seen in Figure 6, as an exit for the fluid W from the cavity 36.
  • the technician may need to repeat the aforementioned method any number of times to remove the foreign material F entirely.
  • the present invention could use alternate steps to dislodge the foreign material F.
  • a technician could use an implement, such as a pick, to enter the cavity 36 and to physically contact the foreign material F.
  • the technician could insert the implement through the additional opening 48, although the other openings are also available. Entering the cavity 36 through the additional opening 48 may require the additional opening 48 to have a different location or shape than that described above.
  • the additional opening could be directed towards the foreign material F to assist insertion of the implement.
  • Another step in a possible method is to close the additional opening 48.
  • the technician could use any suitable technique to close the additional opening 48.
  • suitable techniques include, for example, weld build-up, a weld plug, transient liquid phase bonding and brazing a filler material therein.
  • Figure 7 displays the turbine blade 22 after closing the additional opening 48.
  • the turbine blade 22 now has a repaired section 58 that was once the additional opening 48.
  • the additional opening was a temporary feature on the turbine blade 22.
  • the repaired turbine blade 22 mirrors the turbine blade before the repair, except for the foreign material F.
  • the present invention allows for the salvage of turbine blades 22 that, due to the presence of the foreign material F in the cavity 36, would typically require scrapping.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP05251713A 2005-03-21 2005-03-21 Verfahren zum Präparieren, Reinigen und Reparieren eines Artikels Expired - Fee Related EP1704933B1 (de)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP05251713A EP1704933B1 (de) 2005-03-21 2005-03-21 Verfahren zum Präparieren, Reinigen und Reparieren eines Artikels

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP05251713A EP1704933B1 (de) 2005-03-21 2005-03-21 Verfahren zum Präparieren, Reinigen und Reparieren eines Artikels

Publications (2)

Publication Number Publication Date
EP1704933A1 true EP1704933A1 (de) 2006-09-27
EP1704933B1 EP1704933B1 (de) 2012-12-19

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Family Applications (1)

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EP05251713A Expired - Fee Related EP1704933B1 (de) 2005-03-21 2005-03-21 Verfahren zum Präparieren, Reinigen und Reparieren eines Artikels

Country Status (1)

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EP (1) EP1704933B1 (de)

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5679174A (en) * 1995-10-27 1997-10-21 Chromalloy Gas Turbine Corporation Process and apparatus for cleaning gas turbine engine components
DE19801804A1 (de) * 1998-01-19 1999-07-22 Siemens Ag Turbinenschaufel sowie Verfahren zur Inspektion und/oder Reinigung einer Turbinenschaufel
US20020076097A1 (en) * 2000-12-15 2002-06-20 Janakiraman Vaidyanathan Process and apparatus for locating coated cooling holes on turbine vanes
US20020090298A1 (en) * 2000-12-22 2002-07-11 Alexander Beeck Component of a flow machine, with inspection aperture

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5679174A (en) * 1995-10-27 1997-10-21 Chromalloy Gas Turbine Corporation Process and apparatus for cleaning gas turbine engine components
DE19801804A1 (de) * 1998-01-19 1999-07-22 Siemens Ag Turbinenschaufel sowie Verfahren zur Inspektion und/oder Reinigung einer Turbinenschaufel
US20020076097A1 (en) * 2000-12-15 2002-06-20 Janakiraman Vaidyanathan Process and apparatus for locating coated cooling holes on turbine vanes
US20020090298A1 (en) * 2000-12-22 2002-07-11 Alexander Beeck Component of a flow machine, with inspection aperture

Also Published As

Publication number Publication date
EP1704933B1 (de) 2012-12-19

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