US3031844A

US3031844A - Split combustion liner

Info

Publication number: US3031844A
Application number: US49400A
Authority: US
Inventors: William A Tomolonius
Original assignee: Individual
Current assignee: Individual
Priority date: 1960-08-12
Filing date: 1960-08-12
Publication date: 1962-05-01
Anticipated expiration: 1979-05-01

Description

May 1, 1962 w. A. TOMOLONIUS SPLIT COMBUSTION LINER 3 Sheets-Sheet 1 Filed Aug. 12. 1960 INVENTOR WILL/AM A. TOMOLO/V/US y 1, 1962 w. A. TOMOLONIUS 3,031,844

SPLIT COMBUSTION LINER Filed Aug. 12. 1960 3 Sheets-Sheet 2 INVENTOR WILLIAM A. T OMOLON/US gQQZZZ QW AGENTS May 1, 1962 w. A. TOMOLONIUS SPLIT COMBUSTION LINER Filed Aug. 12. 1960 5 Sheets-Sheet s INVENTOR WILLIAM A. TOMOLO/V/US GQQ.

AGENTS United States Patent Ofiice 3,031,844 Patented May 1, 1962 3,031,844 SPLlT CGMBUSTION LINER William A. Tomolonius, North Reading, Mass, assignor, by mesne assignments, to the United States of America as represented by the Secretary of the Navy Filed Aug. 12, 1969, er. No. 49,490 Ciairns. (Cl. 6G39.69)

The present invention relates to a combustion liner and more particularly to a split combustion liner which may readily be removed without prior removal of the turbine assembly.

Prior to this invention it has been the practice in the art to make full annular type combustion liners of a single unitary construction. Such design necessitated the removal of the turbine assembly prior to removing the old combustion liner when it was necessary to make a replacement or to make a thorough inspection of the condition of the combustion liner.

The instant invention eliminates the above noted disadvantages by making a sectional combustion liner. The combustion liner is made in two sections with fastening means for holding the sections in position. A pair of overlapping plates are bolted to the upper and lower portions of said combustion liner to securely hold them in position.

Since combustion liners are subject to high temperatures and therefore need to be frequently inspected to determine whether or not replacement is necessary, it can therefore be readily seen that a combustion liner that could be removed, inspected and/ or replaced without the removal of the turbine assembly would be very desirous since a considerable amount of time and money could be saved thereby.

An object of the present invention is the provision of a combustion liner which is easy to manufacture and can be produced at a relatively low cost.

A further object of the invention is the provision of a split combustion liner which permits inspection and replacement without prior removal of the entire turbine assembly.

Still another object of the invention is the provision of a combustion liner which utilizes an overlapping spaced flange for hot region fastening of parts.

Other objects and many of the attendant advantages of this invention will be readily appreciated as the same becomes better understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

FIG. 1 shows an assembled View of a preferred embodiment of the invention.

FIG. 2 shows the present invention of FIG. 1 disassembled.

FIG. 3 illustrates the preferred embodiment of the invention with parts removed.

FIG. 4 is a sectional View taken on the line 4-4 of FIG. 1.

FIG. 5 is a sectional view taken on the line 55 of FIG. 3.

FIG. 6 is a sectional view taken on the line 6-6 of FIG. 3.

Referring now to the drawings, wherein like reference characters designate like or corresponding parts through out the several views, there is shown in FIG. 1 an assembled combustion liner 2 which is formed of two sections, namely, a left-hand section 3 and a right-hand section 4. Each section is formed by an inner shell 5 and an outer shell 6 which are semi-circular in shape and are spaced from each other a predetermined distance by a channel shaped semi-circular member 7. It is this member 7 that spaces the inner shell 5 and the outer shell 6 thus forming the combustion chamber 21. The channel shaped member 7 is provided with a plurality of apertures 8 which permit air to enter the space between the inner shell 5 and the outer shell 6 into the combustion chamber 21, the inner shell 5 and the outer shell 6 being fixedly secured to the channel shaped members 7 by welding or some other suitable means of attachment.

The sections 3 and 4 are each provided with a pair of fastening tabs 9 that are secured to the outer face of the channel member 7. Fastening tabs 9 mate when the sections 3 and 4 are properly aligned and they are then secured together by holding bolts 11. The manner in which the inner joint 14 holds the inner shell 5 together will be further explained below.

The outer shell 6 of each section 3 and 4 is provided with a pair of outer flanges 20. The purpose of the outer flanges 26 is to receive the dome plates 13 which complete the outer shell 6 when fastened together by flange bolts 10.

FIG. 2 shows the combustion liner 2 disassembled to better illustrate the manner in which the various components fit together. From this view it can readily be seen how dome plates 13 of the outer shell 6 overlap the inner flange 14 of the inner shell 5 and provide access thereto when dome plates 13 are removed.

FIG. 3 is a view similar to FIG. 1 except here the upper dome plate 13 has been removed to show the inner joint 14- of the inner shell 5. The inner joint 14 is fastened together by a plurality of recessed counter head bolts 15.

FIG. 4 is a sectional view taken along the line 4-4 of FIG. 1. This view clearly shows the outer joint 12 and the manner in which the flange 20 of the dome plates 13 and the flange 20 of the outer shell 6 engage each other to form the outer joint 12. Once the flanges 20 are properly aligned, the bolts 10 are inserted through the flanges 2i and then secured together. This type of flange connection is located at four places, two such flanges 20 holding each dome plate 13 to the outer shell 6.

FIG. 5 is a sectional view taken on line 5-5 of FIG. 3 showing the manner in which the inner joint 14 is secured. As shown, the inner shell 5 of the right-hand section 4 is overlapped by the inner shell 5 of the left hand section 3. Both sections 3 and 4 are provided with a plurality of holes 16 through which recessed counter head bolts 15 are inserted and then fastened by means of nuts 18. The left-hand section 3 of the inner shell 5 is provided with dimples 19 to receive the flat head bolts 15.

The use of air pick-up louvers directly in front of dimples 19 and counter sunk bolt heads15 provide a film of cooling air over the top of the bolts and allows this type of holding mechanism to function in extremely hot flame conditions. The overlapping of flanges also picks up air for cooling. In addition to these advantages, the overlap on the inner shell permits less precision to be required in holding tolerances on the sheet metal parts.

As an alternative form, the inner joints 14 and outer joints 12 may be reduced to tabs, or special fasteners with holes or covering sleeves, to direct air for cooling on both outer and inner shells.

FIG. 6 which is a sectional view taken on the line 6-6 of FIG. 3 shows the combustion chamber 21 and the manner in which the inner shell 5 and the outer shell 6 combine with the channel shaped member 7 to form the combustion chamber 21. As pointed out above, the member 7 is provided with a plurality of apertures 8 which serve as air inlet openings to the combustion chamber 21. The inner shell 5 and outer shell 6 are also provided with a plurality of openings 22 which permit additional air to enter into combustion chamber 21.

After combustion takes place within chamber 21 the hot gases exit via outlet 23 which is of reduced area relative to the cross-sectional area of chamber 21.

As previously stated above, the instant invention permits the removal of a full annular type combustion liner from a jet engine without prior removal of the turbine assembly. The manner in which this is accomplished is by first removing the outer combustion casing of the jet engine (not shown). After this is done, the combustion liner outer shell 6 is exposed. Then the flange bolts 10 are removed, permitting the dome plates 13 to be removed. Upon removing dome plates 13, the inner joint 14 isexposed and the recessed bolts 15 are then removed. After this is done, the holding bolts 11 are removed thus splitting the annular combustion liner into two sections, sections 3 and 4.

It is to be noted that only the upper-half of the liner has been unfastened, however, and it is to be understood that the same steps are to be taken on the lower-half of the liner also.

After the upper and lower halves have been unfastened, then the sections may be rotated and manipulated in such a manner as to permit the liner to be removed in two sections without prior removal of the turbine assembly.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. It is therefore to be understood that Within the scope of the appended claims, the invention may be practiced otherwise than as specifically described.

What is claimed is:

1. In an engine having a turbine assembly, a compressor assembly, an annular combustion liner having spaced perforate inner and outer shells forming a combustion chamber therebetween, the improvement in said annular combustion liner comprising a first and second semi-cylindrical section, each of said sections having an inner and outer shell, said outer shells having a flange at each end and extending over a lesser degree of arc than said inner shells, said flanges having holes therein for receiving fastening bolts, a pair of dome plates having a flange at each end, said flanges having holes therein permitting said dome plates to be fastened to said outer shells to complete said outer shell, inner joint means for releasably fastening said inner shells of said first and second sections, means for cooling said inner joint means, said flanges on said outer shells and said dome plates cooperating to form the outer joint means for releasably fastening said dome plates to said outer shells of said first and second sections, said dome plates being of sufficient width to provide access to said inner joint means whereby said first and second sections may be readily removed from an engine without prior removal of said turbine assembly.

2. In an engine having a turbine assembly, a compressor assembly, an annular combustion liner having spaced perforate inner and outer shells forming a combustion chamber therebetween, the improvement in said annular combustion liner comprising a first and second semi-cylindrical section, each of said sections having a perforate inner and outer shell, said outer shells having a flange at each end and extending over a lesser degree of arc than said inner shells, said flanges having holes therein for receiving fastening bolts, a pair of dome plates, said dome plates having a flange at each end, said flanges having holes therein permitting said dome plates to be fastened to said outer shells to complete said outer shell a pair of semi-circular channel shaped members having apertures therein spacing said inner and outer shells a predetermined distance, said shells being fixedly secured at one end to said channel shaped members, inner joint means for releasably fastening said inner shells of said first and second sections, means for cooling said inner joint means, said flanges on said outer shells and said dome plates cooperating to form the outer joint means for releasably fastening said dome plates to said outer shells of said first and second sections, said dome plates being of sufiicient width to provide access to said inner joint means whereby said first and second sections may be readily removed from an engine without prior removal of said turbine assembly.

3. In a device as described in claim 2 wherein said inner joint means for releasably fastening said inner shells of said first and second sections is formed by said inner shell of said first section overlapping said inner shell of said second section, the overlapping portions of said shells having a plurality of aligned apertures for receiving fastening bolts.

4. In a device as described in claim 3 wherein said means for cooling said inner joint means is formed by said first section overlapping said second section in such a manner as to scoop up air passing therethrough whereby this type of joint means can function properly in extremely hot flame regions.

5. In a device as described in claim 2 wherein said means for cooling said inner joint means is formed by said first section overlapping said second section in such a manner as to scoop up air passing therethrough whereby this type of joint means can function in extremely hot flame regions.

References Cited in the file of this patent UNITED STATES PATENTS 58,648 Joy Oct. 9, 1866 2,537,054 Hildestad Jan. 9, 1951 2,645,081 McDonald July 14, 1953 2,760,338 Keast Aug. 28, 1956 2,988,886 Hamm June 20, 1961