US20080099358A1 - Blade handling tray insert - Google Patents

Blade handling tray insert Download PDF

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Publication number
US20080099358A1
US20080099358A1 US11/586,157 US58615706A US2008099358A1 US 20080099358 A1 US20080099358 A1 US 20080099358A1 US 58615706 A US58615706 A US 58615706A US 2008099358 A1 US2008099358 A1 US 2008099358A1
Authority
US
United States
Prior art keywords
tray
tray insert
handling
gas turbine
insert
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
Application number
US11/586,157
Inventor
David L. Bell
Michael John Niro
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
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
Priority to US11/586,157 priority Critical patent/US20080099358A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: BELL, DAVID L., NIRO, MICHAEL JOHN
Publication of US20080099358A1 publication Critical patent/US20080099358A1/en
Abandoned legal-status Critical Current

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Classifications

    • BPERFORMING OPERATIONS; TRANSPORTING
    • B65CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65DCONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
    • B65D25/00Details of other kinds or types of rigid or semi-rigid containers
    • B65D25/02Internal fittings
    • B65D25/10Devices to locate articles in containers
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B65CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65DCONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
    • B65D25/00Details of other kinds or types of rigid or semi-rigid containers
    • B65D25/02Internal fittings
    • B65D25/10Devices to locate articles in containers
    • B65D25/107Grooves, ribs, or the like, situated on opposed walls and between which the articles are located
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B65CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65DCONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
    • B65D2585/00Containers, packaging elements or packages specially adapted for particular articles or materials
    • B65D2585/68Containers, packaging elements or packages specially adapted for particular articles or materials for machines, engines, or vehicles in assembled or dismantled form
    • B65D2585/6802Containers, packaging elements or packages specially adapted for particular articles or materials for machines, engines, or vehicles in assembled or dismantled form specific machines, engines or vehicles
    • B65D2585/6875Containers, packaging elements or packages specially adapted for particular articles or materials for machines, engines, or vehicles in assembled or dismantled form specific machines, engines or vehicles engines, motors, machines and vehicle parts
    • BPERFORMING OPERATIONS; TRANSPORTING
    • B65CONVEYING; PACKING; STORING; HANDLING THIN OR FILAMENTARY MATERIAL
    • B65DCONTAINERS FOR STORAGE OR TRANSPORT OF ARTICLES OR MATERIALS, e.g. BAGS, BARRELS, BOTTLES, BOXES, CANS, CARTONS, CRATES, DRUMS, JARS, TANKS, HOPPERS, FORWARDING CONTAINERS; ACCESSORIES, CLOSURES, OR FITTINGS THEREFOR; PACKAGING ELEMENTS; PACKAGES
    • B65D81/00Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents
    • B65D81/02Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage
    • B65D81/05Containers, packaging elements, or packages, for contents presenting particular transport or storage problems, or adapted to be used for non-packaging purposes after removal of contents specially adapted to protect contents from mechanical damage maintaining contents at spaced relation from package walls, or from other contents

Abstract

A tray insert for securing fluid reaction members in a handling tray includes a body having first and second major surfaces, first and second ends, sliding members disposed on the first and second ends, which are configured to engage with a plurality of slots formed in the handling tray, and a first plurality of sockets extending into the first major surface, which are spaced from one another to receive and support a plurality of fluid reaction members. The tray insert is configured to hold the fluid reaction members in a suspended state, which prevents them from coming into contact with each other or a surface of the handling tray.

Description

    BACKGROUND OF THE INVENTION
  • This invention relates generally to a tray insert. More particularly this invention relates to a tray insert for securing gas turbine engine blades in a handling tray.
  • During operation of a gas turbine engine, fuel is combusted in compressed air created by a compressor to produce heated gases. The heated gases move in a downstream/aft direction past stator vanes and are used to turn turbine blades to produce rotational power for, among other things, operating the compressor. Turbine blades include a root portion, which is commonly shaped like a “fir tree,” for engaging with a rotor disk and an airfoil portion for positioning within the gas path of the engine.
  • Due to design complexity, gas turbine engines have high manufacturing costs. Therefore, fluid reaction members, such as blades and vanes, are expensive. In addition, the elongated configuration of the airfoil portion of gas turbine engine blades makes them fragile and susceptible to damage. As a result, when moving or transporting gas turbine engine blades, the handler must be extremely careful.
  • Known devices and methods for handling gas turbine engine blades are potentially problematic because it is possible for the airfoil portions of the blades to come into contact with each other, causing damage to one or multiple blades. Also, since the airfoil portions of the blades are in contact with surfaces of the receptacle containing the blades, such as a tray, damage to the blades may be incurred when the tray is inappropriately handled. When Process Incidental Damage (PID) occurs, both time and money are lost, as the blades then need to be replaced.
  • Therefore, it is desired to provide a blade handling tray insert, which enables gas turbine engine fluid reaction members, especially blades and vanes, to be safely and easily handled, thereby reducing PID.
  • BRIEF SUMMARY OF THE INVENTION
  • The present invention is a tray insert for securing fluid reaction members in a handling tray. The tray insert includes a body having first and second major surfaces and first and second ends, sliding members disposed on the first and second ends, which are configured to engage with a plurality of slots formed in the handling tray and a first plurality of sockets extending into the first major surface, which are spaced from one another to receive and support a plurality of fluid reaction members. The tray insert is configured to hold the fluid reaction members in a suspended state, which prevents them from coming into contact with each other or a surface of the handling tray.
  • BRIEF DESCRIPTION OF THE DRAWINGS
  • FIG. 1A is a perspective view of an exemplary embodiment of a blade handling tray insert.
  • FIG. 2 is a top view of a handling tray containing the tray insert securing a first blade and receiving a second blade.
  • FIG. 3 is a top view of the handling tray containing the tray insert securing two blades.
  • DETAILED DESCRIPTION
  • In general, the present invention provides a tray insert for securing fluid reaction members in a handling tray. The tray insert is designed to hold the fluid reaction members, in particular gas turbine engine blades, in a suspended state. This prevents the fluid reaction members from being damaged during handling and/or shipping.
  • FIG. 1 is a perspective view of an exemplary embodiment of blade handling tray insert 10. Tray insert 10 includes first major surface 12A, second major surface 12B, first end 14A and second end 14B. First plurality of sockets 16A extend into first major surface 12A. Second plurality of sockets 16B extend into second major surface 12B. Sliding member 18A is disposed on first end 14A. (A second sliding member, sliding member 18B, is disposed on second end 14B, but cannot be seen from this perspective.)
  • Tray insert 10 is configured to securely hold a plurality of gas turbine engine blades. Sockets 16A, 16B are each designed to receive a portion of a blade. The spacing of sockets 16A, 16B can vary depending upon the size of the blades (or other types of fluid reaction members) which need to be secured for handling. In the exemplary embodiment shown in FIG. 1, there are ten sockets 16A and ten sockets 16B. However, it should be understood that the number of sockets will vary according to the desired application.
  • In addition, in the exemplary embodiment shown in FIG. 1, tray insert 10 includes first major surface 12A, into which sockets 16A extend, and second major surface 12B, into which sockets 16B extend. Sockets 16A are spaced to receive and secure a first type of gas turbine engine blade, such as a first stage blade. Sockets 16B are configured to receive and secure a second type of gas turbine engine blade, such as a second stage blade. Tray insert 10 may be seated in a handling tray such that first major surface 12A is oriented in an upward direction. In contrast, tray insert 10 may also be seated in a handling tray such that second major surface 12B is oriented in an upward direction. As a result, an appropriate major surface 12A, 12B may be selected depending upon which plurality of sockets 16A, 16B corresponds to the shape and size of the blade to be handled. However, if it is desired that only one type of blade be handled, it should also be understood that plurality of sockets 16A or 16B may extend into only one major surface 12A or 12B of tray insert 10.
  • While tray insert 10 may be comprised of any suitable material, in particular, tray insert 10 may be comprised of a polymeric material, such as polyethylene. When comprised of a plastic type material, tray insert 10 may be produced by an injection molding process.
  • FIG. 2 is a top view of handling tray 20 containing tray insert 10 and demonstrates the blade insertion process. Tray insert 10 includes first major surface 12A, second major surface 12B, first end 14A and second end 14B, first plurality of sockets 16A and sliding members 18A, 18B. Handling tray 20 includes side portions 22A-22D, bottom portion 24 and receiving slots 26. Gas turbine engine blades 28 include root 30, platform 32 and airfoil 34.
  • Tray insert 10 may be seated in handling tray 20 by engaging sliding members 18A, 18B with receiving slots 26, which are formed into the inside surface of side portions 22A-22D of handling tray 20. As can be seen in FIG. 2, side portions 22A-22D of handling tray 20 may comprise a number of receiving slots 26. As a result, tray insert 10 may be placed in numerous positions with respect to handling tray 20 in order to accommodate a variety of blade lengths.
  • Once tray insert 10 is firmly seated within handling tray 20, gas turbine engine blade 26 may be inserted into plurality of sockets 16A. (Although FIG. 2 shows tray insert 10 seated in handling tray 20 such that major surface 12A is oriented in an upward direction, as explained with reference to FIG. 1, tray insert 10 may also be seated in handling tray 20 such that major surface 12B is oriented in an upward direction and plurality of sockets 16B are accessible.) Root 30 of gas turbine engine blade 26 is designed to have a “fir tree” configuration, which engages with a rotor disk. Plurality of sockets 16A are configured to engage with root 30 and therefore, have a corresponding “fir tree” shape. Since root 30 and plurality of sockets 16A have a dovetail relationship, as shown in FIG. 2, gas turbine engine blade 26 is inserted into plurality of sockets 16A by matching up the corresponding shapes and lowering blade gas turbine engine blade 26 downward to engage with plurality of sockets 16A like a puzzle piece. Once gas turbine engine blade 26 and plurality of sockets 16A are properly engaged, gas turbine engine blade 26 may only be disengaged through the same angle of insertion.
  • FIG. 3 is a top view of handling tray 20 containing tray insert 10 as it secures two gas turbine engine blades 26. Tray insert 10 includes first major surface 12A, second major surface 12B, first end 14A and second end 14B, first plurality of sockets 16A and sliding members 18A, 18B. Handling tray 20 includes side portions 22A-22D, bottom portion 24 and receiving slots 26. Gas turbine engine blades 28 include root 30, platform 32 and airfoil 34.
  • As described with respect to FIG. 2, gas turbine engine blades 26 are engaged with plurality of sockets 16A by inserting root 30 into a corresponding socket 16A. When root 30 is properly placed within socket 16A, platform 32 of gas turbine engine blade 26 will sit securely against the surface of tray insert 10. Since root 30 fits snuggly within socket 16A, airfoil 34 is held in a suspended state. This prevents airfoil 34 from coming into contact with other gas turbine engine blades 28 and also prevents airfoil 34 from contacting any surface of handling tray 20. As a result, when handling tray 20 is transported, Process Incidental Damage (PID) is unlikely to occur to gas turbine engine blades 28 because airfoil 34 protected from potential breakage and awareness to the handler is increased due the highly visible state of airfoil 34.
  • Although the present invention has been described with reference to preferred embodiments, workers skilled in the art will recognize that changes may be made in form and detail without departing from the spirit and scope of the invention.

Claims (20)

1. A tray insert for securing fluid reaction members in a handling tray, the tray insert comprising:
a body having first and second major surfaces and first and second ends;
sliding members disposed on the first and second ends, the sliding members being configured to engage with a plurality of slots formed in the handling tray; and
a first plurality of sockets extending into the first major surface and being spaced from one another to receive and support a first plurality of fluid reaction members, wherein the tray insert is configured to hold the first plurality of fluid reaction members in a suspended state, which prevents the fluid reaction members from coming into contact with each other or a surface of the handling tray.
2. The tray insert of claim 1, comprising a second plurality of sockets extending into the second major surface and being spaced from one another to receive and support a second plurality of fluid reaction members.
3. The tray insert of claim 2, wherein the tray insert is insertable into the handling tray such that the first major surface is positioned in an upward orientation allowing the first plurality of sockets to be utilized.
4. The tray insert of claim 2, wherein the tray insert is insertable into the handling tray such that the second major surface is positioned in an upward orientation allowing the second plurality of slots to be utilized.
5. The tray insert of claim 2, wherein the first plurality of sockets are configured to receive a plurality of fluid reaction members having a first configuration and the second plurality of sockets are configured to receive a plurality of fluid reaction members having a second configuration which is different than the first configuration.
6. The tray insert of claim 2, wherein the first and second pluralities of sockets each comprises ten sockets.
7. The tray insert of claim 2, wherein the first and second pluralities of sockets are further configured to receive the plurality of fluid reaction members from a defined angle of insertion.
8. The tray insert of claim 7 wherein the plurality of fluid reaction members may only be disengaged from the first and second pluralities of sockets from the defined angle of insertion.
9. The tray insert of claim 1, wherein the tray insert is further configured to hold the plurality of fluid reaction members in a suspended state in which the fluid reaction members are suspended in an orientation parallel to a bottom surface of the handling tray.
10. The tray insert of claim 1, wherein the tray insert is composed of a polymeric material.
11. A tray insert for securely handling gas turbine engine blades, the tray insert comprising:
a body comprising first and second receiving surfaces and first and second ends wherein the first and second receiving surfaces each comprise a plurality of cavities each configured to mate with and being spaced to support a root portion of a gas turbine engine blade;
sliding connectors located on the first and second ends configured for sliding engagement with a plurality of slots formed in a handling tray; and
wherein the tray insert is configured to hold a plurality of gas turbine engine blades in an orientation which prevents an airfoil portion of each gas turbine engine blade from coming into contact with any surface.
12. The tray insert of claim 11, wherein the tray insert may be seated in the handling tray such that the first receiving surface is positioned in an upward orientation which allows the first plurality of cavities to each receive a root portion of a gas turbine engine blade.
13. The tray insert of claim 11, wherein the tray insert may be seated in the handling tray such that the second receiving surface is positioned in an upward orientation which allows the second plurality of cavities to each receive a root portion of a gas turbine engine blade.
14. The tray insert of claim 11, wherein the first plurality of cavities are configured to each receive a root portion having a first shape and the second plurality of cavities are configured to each receive a root portion having a second shape which is different than the first shape.
15. The tray insert of claim 11, wherein the tray insert is further configured to hold the root portions so that the airfoil portions are suspended in an orientation parallel to a bottom surface of the handling tray.
16. The tray insert of claim 11, wherein the first and second pluralities of cavities are further configured to receive the plurality of gas turbine engine blades from a defined angle of insertion.
17. The tray insert of claim 16 wherein the plurality of gas turbine engine blades may only be disengaged from the first and second plurality of cavities from the defined angle of insertion.
18. The tray insert of claim 11, wherein the tray insert is composed of a polymeric material.
19. A method for securing and handling gas turbine engine blades in a tray insert of a handling tray, the method comprising:
seating the tray insert in the handling tray by inserting sliding members disposed on first and second end of the tray insert into a plurality of slots formed in the handling tray so that a first receiving surface is positioned in an upward orientation; and
inserting root portions of a plurality of gas turbine engine blades into a plurality of cavities extending into the first receiving surface which each have a configuration corresponding to the specific configuration of the root portions and are spaced from each other such that airfoil portions of the gas turbine engine blades are suspended in an orientation which prevents them from coming into contact with each other or any surface of the handling tray.
20. The method of claim 19 wherein root portions of a plurality of gas turbine engine blades may be inserted into a plurality of cavities extending into a second receiving surface depending on the specific configuration of the root portions of the plurality of gas turbine engine blades to be secured.
US11/586,157 2006-10-25 2006-10-25 Blade handling tray insert Abandoned US20080099358A1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
US11/586,157 US20080099358A1 (en) 2006-10-25 2006-10-25 Blade handling tray insert

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US11/586,157 US20080099358A1 (en) 2006-10-25 2006-10-25 Blade handling tray insert
EP07254209A EP1916197A1 (en) 2006-10-25 2007-10-24 Blade handling tray insert

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Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013513051A (en) * 2009-12-03 2013-04-18 シーメンス アクティエンゲゼルシャフト Adaptive transport package
JP2014094755A (en) * 2012-11-08 2014-05-22 Mitsubishi Heavy Ind Ltd Wing body packing method and wing body packing set
US20180086503A1 (en) * 2016-03-25 2018-03-29 Boe Technology Group Co., Ltd. Adjustable packing box and packing method using the same
US20190185256A1 (en) * 2016-11-28 2019-06-20 Mitsubishi Heavy Industries Compressor Corporation Rotor securing jig and rotor storage unit

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN103465103B (en) * 2013-08-24 2016-01-27 浙江易锋机械有限公司 Pxe piston turnover box
CN109353649B (en) * 2018-11-20 2020-02-14 中国航发贵州黎阳航空动力有限公司 Turnover box for processing and turnover of engine blades

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US5423422A (en) * 1994-03-14 1995-06-13 Empak, Inc. Flat panel display container
US5628403A (en) * 1996-01-16 1997-05-13 Bill Thomas Associates, Inc. Universal turbine blade packaging container
US5971151A (en) * 1995-11-27 1999-10-26 Tanaka; Hisayuki Combined holder for displaying and packaging midget lamp assembly
US20060249416A1 (en) * 2005-05-05 2006-11-09 Bradford Judson A Collapsible container having sliding support member assemblies for supporting dunnage

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US6755302B1 (en) * 1998-08-14 2004-06-29 Black & Decker Inc. Tool container
DE10214161C1 (en) * 2002-03-28 2003-05-28 Willibald Hergeth Package for transporting turbine blades of different sizes has frusto-conical sections with surfaces which support blade laid diagonally across section
DE502004004101D1 (en) * 2004-10-05 2007-07-26 Siemens Ag Packaging for delicate parts

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5423422A (en) * 1994-03-14 1995-06-13 Empak, Inc. Flat panel display container
US5971151A (en) * 1995-11-27 1999-10-26 Tanaka; Hisayuki Combined holder for displaying and packaging midget lamp assembly
US5628403A (en) * 1996-01-16 1997-05-13 Bill Thomas Associates, Inc. Universal turbine blade packaging container
US20060249416A1 (en) * 2005-05-05 2006-11-09 Bradford Judson A Collapsible container having sliding support member assemblies for supporting dunnage

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2013513051A (en) * 2009-12-03 2013-04-18 シーメンス アクティエンゲゼルシャフト Adaptive transport package
JP2014094755A (en) * 2012-11-08 2014-05-22 Mitsubishi Heavy Ind Ltd Wing body packing method and wing body packing set
US20180086503A1 (en) * 2016-03-25 2018-03-29 Boe Technology Group Co., Ltd. Adjustable packing box and packing method using the same
US20190185256A1 (en) * 2016-11-28 2019-06-20 Mitsubishi Heavy Industries Compressor Corporation Rotor securing jig and rotor storage unit
US10689187B2 (en) * 2016-11-28 2020-06-23 Mitsubishi Heavy Industries Compressor Corporation Rotor securing jig and rotor storage unit

Also Published As

Publication number Publication date
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Legal Events

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AS Assignment

Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BELL, DAVID L.;NIRO, MICHAEL JOHN;REEL/FRAME:018462/0511

Effective date: 20061024

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION