Claims:CLAIMS

What is claimed is:

1. An adjustable transportation stand assembly for securing aircraft engines, comprising:

a trolley top weldment (102a-102b) is mounted to a trolley base weldment (104a-104b) via a plurality of rubber pads (106a-106b), whereby the trolley base weldment (104a-104b) further connected to at least two pair of wheels (108a-108b) via a plurality of wheel support blocks (120a-120d) with a plurality of locking brackets (122a-122d);

a front support post (110), comprising:

at least one clamp (124a) is mounted to a support post (126), whereby the support post (126) further connected to a front support post table (128), and further the support post (126) is configured to move in horizontal direction with respect to the front support post table (128) in a linear adjustable manner thereby adjusted with respect to a front portion (204) of the engine (202) in a horizontal orientation.

a left hand support post (114a) and a right hand support post (114b), comprising:

a plurality of center rails (148a-148c) mounted to a left hand support post (114a) and a right hand support post (114b), whereby the left hand support post (114a) and the right hand support post (114b) further engaged with the plurality of center rails (148a-148c) in a linear adjustable manner thereby adjusted with respect to the engine (202); and

atleast two trunion support blocks (150a-150b) are mounted to atleast two skyjack support members (152a-152b), whereby the atleast two skyjack support members (152a-152b) are configured to secure the middle portion (208) of the engine (202) in a horizontal orientation.

a rear support post (112) rigidly fixed to the trolley top weldment (102c), comprising:

a support frame (132) is mounted to at least one clamp on a top portion, whereby the at least one clamp further is configured to secure the rear portion (206) of the engine (202) in a horizontal orientation with respect to a vertical adjustable manner; and

a plurality of resting pads (116a-116d) are mounted at corners of the trolley top weldment (102a-102b), whereby the plurality of resting pads (116a-116d) further includes a plurality of holes (210a-210n) are configured to clamp the engine (202) in a vertical orientation.

2. The assembly of claim 1, wherein the at least one clamp (124a) is further configured to adjust in a vertical direction with respect to the support post (126) for orientating the engine in the horizontal direction.

3. The assembly of claim 1, wherein the at least one clamp (124a) further includes a plurality of holes (130a-130n) for clamping the front portion (204) of the engine (202) in a horizontal orientation.

4. The assembly of claim 1, wherein the at least two trunion support blocks (150a-150b) further mounted on a top portion of the left hand support post (114a) and the right hand support post (114b).

5. The assembly of claim 1, wherein the at least two skyjack support members (152a-152b) further include circular slots (154a-154b) for accommodating the atleast two trunion support blocks (150a-150b).

6. The assembly of claim 1, wherein the plurality of resting pads (116a-116d) is further connected to a plurality of base plates (160a-160d) are configured to secure the engine (202) in a vertical orientation.

7. The assembly of claim 1, wherein a tow bar (118) is attached to the trolley base weldment (104a-104b) and is further attached to a pulling link (162a-162b) is configured to turns the two pair of wheels (108a-108d) to allow the movement in desired direction by automatic force generating by means of a motor.

8. An adjustable transportation stand assembly for securing aircraft engines, comprising:

a trolley top weldment (102a-102b) is mounted to a trolley base weldment (104a-104b) via a plurality of rubber pads (106a-106b), whereby the trolley base weldment (104a-104b) further connected to at least two pair of wheels (108a-108b) via a plurality of wheel support blocks (120a-120d) with a plurality of locking brackets (122a-122d);

a front support post (110), comprising:

at least one clamp (124a) is mounted to a support post (126), whereby the support post (126) further connected to a front support post table (128), and further the support post (126) is configured to move in horizontal direction with respect to the front support post table (128) in a linear adjustable manner thereby adjusted with respect to a front portion (204) of the engine (202) in a horizontal orientation.

a left hand support post (114a) and a right hand support post (114b), comprising:

a plurality of center rails (148a-148c) mounted to a left hand support post (114a) and a right hand support post (114b), whereby the left hand support post (114a) and the right hand support post (114b) further engaged with the plurality of center rails (148a-148c) in a linear adjustable manner thereby adjusted with respect to the engine (202); and

atleast two trunion support blocks (150a-150b) are mounted to atleast two skyjack support members (152a-152b), whereby the atleast two skyjack support members (152a-152b) are configured to secure the middle portion (208) of the engine (202) in a horizontal orientation.

a rear support post (112) non- rigidly fixed to the trolley top weldment (102c), comprising:

a plurality of center rails mounted to the rear support post (112), whereby the rear support post (112) further engaged with the plurality of center rails (156a-156c) in a linear adjustable manner thereby adjusted with respect to the rear portion engine (206) in a horizontal orientation; and

a plurality of resting pads (116a-116d) are mounted at corners of the trolley top weldment (102a-102b), whereby the plurality of resting pads (116a-116d) further includes a plurality of holes (210a-210n) are configured to clamp the engine (202) in a vertical orientation.

9. The assembly of claim 1 and claim 8, wherein the rear support post (112) further includes a plurality of adjustable locking pins (142a-142n) are configured to lock the rear support post (112) for securing the rear portion (206) of the engine (202) in a horizontal orientation.

10. A method for securing aircraft engines in a horizontal orientation, comprising:

preparing an engine stand (100) for the defined engine configuration;

setting the dimensions as per the engine horizontal configuration and lock all the mounting positions;

placing the engine (202) in a horizontal equilibrium position;

mounting the engine on a front support post (110), a rear support post (112), a left hand support post (114a) and a right hand support post (114b) in the equilibrium manner;

clamping a front portion (204) of the engine (202) in a horizontal orientation with respect to a linear adjustable manner of the front support post (110);

clamping a middle portion (208) of the engine (202) in the horizontal orientation with respect to the left hand support post (114a) and the right hand support post (114b) are engaged with a plurality of center rails (148a-148c) in the linear adjustable manner; and

clamping a rear portion (206) of the engine (202) in the horizontal orientation with respect to a support frame (132) of the rear support post (112) in a vertical adjustable manner.

11. A method for securing aircraft engines in a vertical orientation, comprising:

preparing an engine stand (100) for the defined engine configuration;

setting the dimensions as per the engine vertical configuration and lock all the mounting positions;

placing the engine (202) in a vertical equilibrium position;

mounting the engine (202) on a four corners of a trolley top weldment (102a-102d) with respect to a plurality of resting pads (116a-116d); and

clamping the engine (202) in the vertical orientation with respect to a plurality of holes (210a-210d) secure within the plurality of resting pads (116a-116d). , Description:DESCRIPTION
TECHNICAL FIELD

[001] The present disclosure generally relates to the field of aircraft engine stand assemblies used for secure mounting of an aircraft engine. More particularly, the present disclosure relates to an adjustable transposition stand assembly for securing various aircraft engines configuration in different orientations to facilitate transport and repair operations in maintenance, repair and overhaul (MRO) facilities.

BACKGROUND

[002] Generally, the engines have a variety of sizes, shapes and weights. The aircraft engines need to be transported from one location to another location within a plant. As such, engine stands are generally designed to transport various engines in different configurations to facilitate transport of engine from one building to other within the MRO plant (Maintenance, repair overhaul).

[003] Traditional engine stands take more time for loading and unloading of the engine. Most of the engine stands are designed exclusively for a particular engine model. Some engine stands are able to remain upright and secure during shipping within the MRO plant. But the engines containing different sizes and at different heights require multiple stands during transportation. There are no available engine stands that can be used to lift different engines and also carry multiple types of engines for transporting within the MRO plant (Maintenance, repair and overhaul). Moreover, this also increases the time taken for loading and unloading the engine on and off the equipment.

[004] In the light of aforementioned brief details, there exists a need for an assembly that would overcome or ameliorate the above mentioned disadvantages.

BRIEF SUMMARY

[005] The following is a simplified summary of the disclosure in order to provide a basic understanding to the reader. This summary is not an extensive overview of the disclosure and it does not identify key/critical elements of the invention or delineate the scope of the invention. Its sole purpose is to present some concepts disclosed herein in a simplified form as a prelude to the more detailed description that is presented later.

[006] Exemplary embodiments of the present disclosure are directed towards a universal aero engine transportation stand.

[007] According to an exemplary embodiment of the present disclosure, the assembly includes a trolley top weldment (102a-102b) mounted to a trolley base weldment (104a-104b) via a plurality of mounting brackets with rubber pads (106a-106n), whereby the trolley base weldment (104a-104b) is further connected with two pair of low noise making wheels (108a-108d), which are specially designed for this kind of shop floor application via a plurality of wheel support blocks (120a-120d) with a plurality of locking brackets (122a-122d) and the trolley base weldment (104a-104b) further includes a plurality of forklift slots (140a-140n) for lifting the aero engine stand if the two pair of wheels (108a-108d) is absent.

[008] According to an exemplary embodiment of the present disclosure, the assembly further includes a front support post (110), comprising: at least one clamp (124a) mounted on a support post (126), whereby the support post (126) further connected to a front support post table (128), and further the support post (126) is configured to move in a horizontal direction with respect to the front support post table (128) in a linear adjustable manner thereby adjusted with respect to a front portion (204) of the engine (202) in a horizontal orientation.

[009] Another exemplary embodiment of the present disclosure, the assembly further includes a left hand support post (114a) and a right hand support post (114b) are mounted to a plurality of center rails (148a-148c), whereby the left hand support post (114a) and the right hand support post (114b) further engaged with the plurality of center rails (148a-148c) in a linear adjustable manner thereby adjusted with respect to the engine (202); and two trunion support blocks (150a-150b) are mounted on a top portion of the left hand support post (114a) and the right hand support post (114b), and the two trunion support blocks (150a-150b) are further mounted to the two skyjack support members (152a-152b) that is configured to secure the middle portion (208) of the engine (202) in a horizontal orientation.

[0010] Another exemplary embodiment of the present disclosure, the assembly further includes a rear support post (112) rigidly fixed to the trolley top weldment (102c), and the rear support post (112) comprising, a support frame (132) is mounted on a top portion of the rear support post (112). The support frame (132) further is configured to move in a vertical adjustable manner thereby adjusted with respect to the engine (202), whereby the support frame (132) further mounted to at least one clamp (124b) is configured to secure the rear portion (206) of the engine (202) in a horizontal orientation.

[0011] Another exemplary embodiment of the present disclosure, the rear support post (112) further non-rigidly fixed to the trolley top weldment (102c) and the rear support post (112) further configured to engage with the multiple center rails (156a-156c) in a linear adjustable manner thereby adjusted with respect to the rear portion engine (206) in a horizontal orientation.

[0012] Yet another exemplary embodiment of the present disclosure, the assembly further includes a plurality of resting pads (116a-116d) is mounted on corners of the trolley top weldment (102a-102b), whereby the plurality of resting pads (116a-116d) further include a plurality of holes (210a-210n) are configured to clamp the engine (202) in a vertical orientation.

[0013] An objective of the present disclosure is directed towards an assembly for transporting or shipping the engine from one building to other within the MRO plant (Maintenance, repair and overhaul).

[0014] Another objective of the present disclosure is directed towards an assembly for repairing the aircraft engines within the MRO plant without any disturbance from supporting wheels by means of the supporting wheels fold to top side.

[0015] Another objective of the present disclosure is directed towards an assembly that may be manufactured in a cost-effective manner by using materials like structural steel and other grades of steel or alternative materials that are commercially available.

BRIEF DESCRIPTION OF DRAWINGS

[0016] Other objects and advantages of the present invention will become apparent to those skilled in the art upon reading the following detailed description of the preferred embodiments, in conjunction with the accompanying drawings, wherein like reference numerals have been used to designate like elements, and wherein:

[0017] FIG. 1A and FIG. 1B are diagrams depicting an adjustable transportation stand assembly for securing aircraft engines, in accordance with one or more embodiments.

[0018] FIG. 2A- FIG. 2B are diagrams depicting the adjustable transportation stand assembly with the engine in different orientations, in accordance with one or more embodiments.

[0019] FIG. 3A and FIG. 3B are diagrams depicting exploded views of adjustable transportation stand assembly, in accordance with one or more embodiments.

[0020] FIG. 4 is an exploded view of a wheel support assembly, in accordance with one or more embodiments.

[0021] FIG. 5A and FIG.5B are exploded views of a front support post, in accordance with one or more embodiments.

[0022] FIG. 6A and FIG. 6B are exploded views of a right hand support post, in accordance with one or more embodiments.

[0023] FIG. 7A and FIG.7B are exploded views of a rear support post, in accordance with one or more embodiments.

[0024] FIG. 7C is another exploded view of the rear support post, in accordance with one or more embodiments.

[0025] FIG. 8 is a flow diagram depicting a method for securing the aircraft engines in a horizontal orientation, in accordance with one or more embodiments.

[0026] FIG. 9 is a flow diagram depicting a method for securing aircraft engines in a vertical orientation, in accordance with one or more embodiments.

DETAILED DESCRIPTION

[0027] It is to be understood that the present disclosure is not limited in its application to the details of construction and the arrangement of components set forth in the following description or illustrated in the drawings. The present disclosure is capable of other embodiments and of being practiced or of being carried out in various ways. Also, it is to be understood that the phraseology and terminology used herein is for the purpose of description and should not be regarded as limiting.

[0028] The use of “including”, “comprising” or “having” and variations thereof herein is meant to encompass the items listed thereafter and equivalents thereof as well as additional items. The terms “a” and “an” herein do not denote a limitation of quantity, but rather denote the presence of at least one of the referenced item. Further, the use of terms “first”, “second”, and “third”, and the like, herein do not denote any order, quantity, or importance, but rather are used to distinguish one element from another.

[0029] Referring to FIG. 1A and FIG. 1B are diagrams 100a-100b, depicting an adjustable transportation stand assembly for securing aircraft engines, in accordance with one or more embodiments. The adjustable mounting assembly 100 comprises a trolley top weldment 102a-102b, a trolley base weldment 104a-104b, multiple mounting brackets with rubber pads 106a-106n, two pair of wheels 108a-108d, a front support post 110, a rear support post 112, a left hand support post 114a, a right hand support post 114b, multiple resting pads 116a-116d and a tow bar 118. The trolley top weldment 102a-102b mounted to a trolley base weldment 104a-104b via multiple mounting brackets with rubber pads 106a-106n. The trolley base weldment 104a-104b further connected to the two pair of wheels 108a-108d via multiple wheel support blocks 120a-120d with multiple locking brackets 122a-122d. The trolley base weldment 104a-104b further includes multiple forklift slots 140a-140n for lifting the aero engine stand if the two pair of wheels 108a-108d is absent.

[0030] As shown in FIG. 1A and FIG. 1B, the front support post 110 includes a clamp 124a that is mounted on a support post 126. The support post 126 is connected to a front support post table 128. The support post 126 is further configured to move in a horizontal direction with respect to the front support post table 128 in a linear adjustable manner thereby adjusted with respect to a front portion of the engine (not shown) in the horizontal orientation. The clamp 124a is further configured to adjust in a vertical direction with respect to the support post 126 for orientating the engine (not shown) in the horizontal direction. The clamp 124a further includes multiple holes 130a-130n for clamping the front portion of the engine (not shown) in the horizontal orientation.

[0031] As shown in FIG. 1A, the rear support post 112 rigidly fixed to the trolley top weldment 102c. The rear support post 112 includes a support frame 132 is mounted on a top portion of the rear support post 112. The support frame 132 further is configured to move in a vertical adjustable manner thereby adjusted with respect to the engine (not shown). The support frame 132 further mounted to at least one clamp 124b is configured to secure the rear portion of the engine (not shown) in a horizontal orientation. The rear support post 112 further includes multiple adjustable locking pins 142a-142n is configured to lock the rear support post 112 for securing the engine (not shown) in the horizontal orientation.

[0032] As shown in FIG. 1B, another embodiment of the rear support post 112 further non-rigidly fixed to the trolley top weldment 102c and the rear support post 112 further configured to engage with the multiple center rails 156a-156c in a linear adjustable manner thereby adjusted with respect to the rear portion engine (not shown) in a horizontal orientation.

[0033] As shown in FIG. 1A and FIG. 1B, a left hand support post 114a and a right hand support post 114b are mounted to multiple center rails 148a-148c. The left hand support post 114a and the right hand support post 114b further engaged with the multiple center rails 148a-148c in a linear adjustable manner thereby adjusted with respect to the engine (not shown). Two trunion support blocks 150a-150b are mounted on a top portion of the left hand support post 114a and the right hand support post 114b. The two trunion support blocks 150a-150b are further mounted to the two skyjack support members 152a-152b are configured to secure the middle portion of the engine (not shown) in a horizontal orientation. The two skyjack support members 152a-152b further include circular slots 154a-154b for accommodating the atleast two trunion support blocks 150a-150b.

[0034] As shown in FIG. 1A and FIG. 1B, the multiple resting pads 116a-116d mounted at corners of the trolley top weldment 102a-102b. The multiple resting pads 116a-116d is further connected to multiple base plates’ 160a-160d for clamping the engine (not shown) in a vertical orientation. The tow bar 118 is attached to the trolley base weldment 104a-104b and is further attached to a pulling link 162a-162b (automatic or manual). The pulling link 162a-162b is configured to turn the wheels to allow the movement in desired direction by automatic force generating (for e.g., a motor). The adjustable mounting assembly for securing the engine in various orientations (for e.g., in a horizontal orientation and a vertical orientation) facilitates transport of engine from one building to other within the MRO plant (Maintenance, repair and overhaul). The two pair of wheels 108a-108d further fold to top side and the trolley base weldment 104a-104b further touch to ground for repairing the aircraft engines within the MRO plant without any disturbance from supporting wheels 108a-108d.

[0035] Referring to FIG. 2A- FIG. 2B are diagrams 200a-200b, depicting the adjustable transportation stand assembly with the engine in different orientations, in accordance with one or more embodiments. For example the diagram 200a depicting the engine 202, the front support post 110 and the rear support post 112, the left hand support post 114a, the right hand support post 114b (not shown) and the skyjack support member 152a. The clamps 124a-124b of the front support post 110 and the rear support post 112 are configured to secure the front portion 204 and a rear portion 206 of the engine 202 in the horizontal orientation. The skyjack support members 152a-152b (152b not shown) of the left hand support post 114a and the right hand support post 114b are configured to secure the middle portion 208 of the engine 202 in the horizontal orientation.

[0036] As shown in FIG. 2B, for example, the diagram 200b depicting the engine 202, multiple resting pads 116a-116d are mounted at corners of the trolley top weldment 102a-102b. The multiple resting pads 116a-116n further include multiple holes 210a-210n are configured to clamp the engine 202 in a vertical orientation.

[0037] Referring to FIG. 3A is a diagram 300a depicting exploded views of adjustable transportation stand assembly, in accordance with one embodiment. The adjustable transportation stand assembly depicting a wheel support assembly 400, a resting pad assembly 116a, front support post portions 500a-500b, right hand support post portions 600a-600b, rear support post portions 700a and 700b.

[0038] Referring to FIG. 3B is a diagram 300b depicting exploded views of adjustable transportation stand assembly, in accordance with another embodiment. The adjustable transportation stand assembly depicting a wheel support assembly 400, a resting pad assembly 116a, front support post portions 500a-500b, right hand support post portions 600a-600b, rear support post portions 700a and 700c.

[0039] Referring to FIG. 4 is an exploded view 400, of a wheel support assembly, in accordance with one or more embodiments. The wheel support assembly 400 includes multiple screws 402a-402n bolted to a rubber pad 106a. The wheel support block 120a is coupled to the trolley base weldment 104a via a locking bracket 122a (as shown in FIG.1).

[0040] Referring to FIG. 5A and FIG.5B exploded views 500a-500b, of the front support post, in accordance with one or more embodiments. The clamp 124a is mounted on a support post 126. The front support post table 128 is locked with multiple screws 502a-502n. The clamp 124a further includes multiple holes 130a-130n for clamping the front portion 204 of the engine 202 (as shown in FIG.2A) in the horizontal orientation.

[0041] Referring to FIG. 6A and FIG. 6B are exploded views 600a-600b, of a right hand support post, in accordance with one or more embodiments. The right hand support post 114b and is mounted to multiple center rails 148a-148c in a linear adjustable manner thereby adjusted with respect to the engine 202 (as shown in FIG.2A). The trunion support block 150b is mounted to the two skyjack support member 152b is configured to secure the middle portion 208 of the engine 202 in a horizontal orientation (as shown in FIG.2A). The skyjack support member 152b further include circular slot 154b for accommodating the trunion support block 150b.

[0042] Referring to FIG. 7A and FIG.7B are exploded views 700a and 700b, of a rear support post, in accordance with one or more embodiments. The rear support post 112 is rigidly fixed to the trolley top weldment 102c. The support frame 132 is configured to move in a vertical adjustable manner thereby adjusted with respect to the engine 202 (as shown in FIG.2A). The support frame 132 is further connected to the clamp 124b and is configured to secure the rear portion 206 of the engine 202 (as shown in FIG.2A) in a horizontal orientation. The multiple adjustable locking pins 142a-142n is configured to lock the rear support post 112 for securing the engine 202 (as shown in FIG.2A) in the horizontal orientation.

[0043] Referring to FIG. 7C is another exploded view 700c, of the rear support post, in accordance with one or more embodiments. The rear support post 112 further non-rigidly fixed to the trolley top weldment 102c and the rear support post 112 further configured to engage with the multiple center rails 156b-156c in a linear adjustable manner thereby adjusted with respect to the rear portion engine 206 (as shown in FIG.2A) in a horizontal orientation.

[0044] Referring to FIG. 8 is a flow diagram 800, depicting a method for securing aircraft engines in a horizontal orientation, in accordance with one or more embodiments. The method starts at step 802 by preparing an engine stand for the defined engine configuration. The method continues to next step 804 by setting the dimensions as per the engine horizontal configuration and lock all the mounting positions. The method continues to next step 806 by placing the engine in a horizontal equilibrium position. The method continues to next step 808 by mounting the engine on a front support post, a rear support post, a left hand support post and a right hand support post in the equilibrium manner. The method continues to next step 810 by clamping the front portion of the engine in a horizontal orientation with respect to a linear adjustable manner of the front support post assembly. The method continues to next step 812 by clamping a middle portion of the engine in the horizontal orientation with respect to the left hand support post and the right hand support post are engaged with multiple center rails in the linear adjustable manner. The method continues to next step 814 by clamping a rear portion of the engine in the horizontal orientation with respect to a support frame of the rear support post in a vertical adjustable manner.

[0045] Referring to FIG. 9 is a flow diagram 900, depicting a method for securing aircraft engines in a vertical orientation, in accordance with one or more embodiments. The method starts at step 902 by preparing an engine stand for the defined engine configuration. The method continues to next step 904 by setting the dimensions as per the engine vertical configuration and lock all the mounting positions. The method continues to next step 906 by placing the engine in a vertical equilibrium position. The method continues to next step 908 by mounting the engine on four corners of the trolley top weldment with respect to multiple resting pads. The method continues to next step 910 by clamping the engine in the vertical orientation with respect to the multiple holes secured within the multiple resting pads.

[0046] More illustrative information will now be set forth regarding various optional architectures and uses in which the foregoing method may or may not be implemented, as per the desires of the user. It should be strongly noted that the following information is set forth for illustrative purposes and should not be construed as limiting in any manner. Any of the following features may be optionally incorporated with or without the exclusion of other features described.

[0047] Although the present disclosure has been described in terms of certain preferred embodiments and illustrations thereof, other embodiments and modifications to preferred embodiments may be possible that are within the principles and spirit of the invention. The above descriptions and figures are therefore to be regarded as illustrative and not restrictive.

[0048] Thus the scope of the present disclosure is defined by the appended claims and includes both combinations and sub combinations of the various features described herein above as well as variations and modifications thereof, which would occur to persons skilled in the art upon reading the foregoing description.