Patent Abstract:
A cowl for use with a combustor of a gas turbine engine, the cowl includes a main body with an annular corrugation. A combustor of a gas turbine engine, the combustor includes: a hollow body defining a combustion chamber, the hollow body having a liner; an outer cowl having an annular corrugation, the cowl connecting to the liner; and an inner cowl connecting to the liner. A method of configuring a cowl for a gas turbine engine combustor, the method includes forming an annular corrugation in a main body of the cowl.

Full Description:
BACKGROUND OF THE INVENTION 
     In a gas turbine engine, pressurized air is provided from the compressor stage to the combustor, whereupon it is mixed with fuel and is burned in the combustion chamber. The amount of pressurized air that enters the fuel/air mixers, and correspondingly the inner and outer passages of the combustor, has typically been regulated by inner and outer cowls located upstream of the fuel/air mixers and the combustor dome. Such cowls have been generally held in place by means of a bolted joint that includes the combustor dome, the cowl, and either the inner or outer combustor liner. Accordingly, both the outer and inner cowls of a gas turbine engine experience a slight change in pressure thereacross, as well as a vibratory load induced by the engine. While these environmental factors have a greater effect on the outer cowl, they nevertheless cause wear on both cowls and consequently limit the life thereof. 
     In addressing this problem, the prior art has generally taken one of the following approaches. The first of which involves use of a sheet metal body for the cowls with a lip formed at the leading edge thereof, preferably by curling or wrapping the sheet metal around a damper wire. However, it has been found that this design is life-limited due to a rubbing-type wear occurring at the interface of the wire and the sheet metal body caused by a thermal mismatch between the wire and the wrap. More specifically, the thermal mismatch causes the sheet metal to unwrap around the wire, creating a gap between the wire and the cowl. In addition, white noise exiting the diffuser and/or combustor acoustics creates high cycle fatigue vibratory loading of the wire against the sheet metal wrap. Thus, the combined rubbing and vibratory induced shaking of the wire against the metal wrap result in the wrapped portion of the cowl thinning, cracking and eventually liberating sheet metal and wire fragments. 
     Another cowl design involves a machined ring that forms the leading edge lip of the cowl, where the ring is welded to a formed sheet metal body. Such a machined ring provides a solid lip for the cowl, which is desirable, but circumferential welding thereof to the formed sheet metal body has resulted in stress concentrations both in and around the weld. 
     A one-piece cowl design is disclosed in a U.S. patent application entitled “One-Piece Combustor Cowl,” U.S. Pat. No. 5,924,288, which discloses a cowl that is casted with a solid lip of increased thickness at a leading edge thereof. While suitable for its intended purpose, this cowl tends to be both heavier and more costly than a sheet metal cowl. 
     SUMMARY OF THE INVENTION 
     The above discussed and other drawbacks and deficiencies are overcome or alleviated by a corrugated cowl. In an exemplary embodiment of the invention, a cowl for use with a combustor of a gas turbine engine, the cowl includes a main body with an annular corrugation. In another exemplary embodiment a combustor of a gas turbine engine, the combustor includes: a hollow body defining a combustion chamber, the hollow body having a liner; an outer cowl having an annular corrugation, the cowl connecting to the liner; and an inner cowl connecting to the liner. A method of configuring a cowl for a gas turbine engine combustor, the method includes forming an annular corrugation in a main body of the cowl. 
    
    
     DESCRIPTION OF THE DRAWING 
     Referring to the exemplary drawings wherein like elements are numbered alike in the several Figures: 
     FIG. 1 is a longitudinal cross-sectional view of a gas turbine engine combustor including an outer cowl with annular corrugations and an inner cowl; 
     FIG. 2 is a forward looking aft view of the cowl depicted in FIG. 1; 
     FIG. 3 is a longitudinal cross-sectional view of a gas turbine engine combustor including an outer cowl with annular corrugations and an inner cowl with annular corrugations; 
     FIG. 4 is a forward looking aft isometric view of both a corrugated outer cowl and a corrugated inner cowl; 
     FIG. 5 is an aft looking forward isometric view of the corrugated outer and inner cowls of FIG. 3; 
     FIG. 6 is an enlarged, partial cross-sectional view of the corrugated cowl depicted in FIG. 1; 
     FIG. 7 is an enlarged, partial cross-sectional view of the corrugated cowl depicted in FIG. 1 illustrated with a full wrap; and 
     FIG. 8 is an alternative embodiment of an enlarged, partial cross-sectional view of the corrugated outer cowl depicted in FIG. 1 illustrated with a partial wrap. 
    
    
     DETAILED DESCRIPTION OF THE INVENTION 
     Referring now to FIG. 1, a single annular combustor  10  suitable for use in a gas turbine engine is illustrated. Combustor  10  includes a hollow body  11  that defines a combustion chamber  12  therein. Hollow body  11  is generally annular in form and includes an outer liner  14 , an inner liner  16 , and a domed end or dome  18 . In the present annular configuration, domed end  18  of hollow body  11  further includes a plurality of air/fuel mixers  20  of known design spaced circumferentially therearound. 
     In combustor  10 , an outer cowl  22  is provided upstream of combustion chamber  12  and attached to outer liner  14 , as well as dome  18 , at outer bolted connection  24 . An inner cowl  26  is also provided upstream of combustion chamber  12  and attached to inner liner  16 , as well as dome  18 , at inner bolted connection  28 . Outer and inner cowls  22  and  26  perform the function of properly directing and regulating the flow of pressurized air from a diffuser of the gas turbine engine to dome  18  and outer and inner passages  30  and  32  located adjacent outer and inner liners  14  and  16 , respectively. It will be understood from FIGS. 1 and 2 that outer and inner cowls  22  and  26  are annular in shape like combustor  10 . As is typical with combustor cowls, outer and inner cowls  22  and  26  are axially elongated relative to a central cowl axis  34 . 
     It is desired that outer and inner cowls  22  and  26  be both lightweight and inexpensive. In order to achieve this, outer and inner cowls  22  and  26  preferably are made of sheet metal. The sheet metal material for outer and inner cowls  22  and  26  may include cobalt based alloys and nickel based alloys. In particular, the preferred Aerospace Material Specifications for such cobalt based alloys include AMS5608 and the preferred Aerospace Material Specifications for such nickel based alloys include AMS5536, AMS5878, and AMS5599. 
     In order to increase the stiffness of outer cowl  22 , outer cowl  22  is molded to form annular corrugations  40 . By increasing the stiffness to outer cowl  22 , the frequency of outer cowl  22  is also increased. There is a proportional correlation of increased stiffness to increased frequency; thus, as stiffness increases, so does the frequency. It is desirable to increase the frequency of outer cowl  22  to a point in which the frequency of outer cowl  22  is higher than the frequency of the engine. 
     Referring to FIG. 3, in an alternative embodiment, both outer and inner cowls  22  and  26  are formed with annular corrugations  40 . FIGS. 4 and 5 illustrate isometric views of outer and inner cowls  22  and  26  with annular corrugations  40 . 
     FIG. 6 illustrates the various parameters to forming annular corrugations in outer cowl  22 . When molding annular corrugations  40 , there are three parameters to annular corrugations  40 : (a) the number of annular corrugations in outer cowl  22 , which is shown as w 1 , w 2 , etc., with the total number of annular corrugations represented by w all ; (b) the height of each annular corrugation  40 , which is shown as “h”; and (c) the spacing of each annular corrugation  40 , which is shown as “s”. The two important parameters for forming annular corrugations  40  are the spacing, s, and the height, h, of annular corrugations  40 . The spacing and height of annular corrugations are optimized so that the natural frequency of outer cowl  22  is increased to outside the engine operating range. The number of corrugations in outer cowl  22  does not significantly affect the stiffness of outer cowl  22 . 
     In an exemplary embodiment, the spacing of annular corrugations is from about 0.010 inches to about 0.500 inches, with a preferred spacing of about 0.080 inches. The height of annular corrugations is from about 0.010 inches to about 0.050 inches, with a preferred height of about 0.0334 inches. By forming annular corrugations with the spacing and height in the above-indicated range, the stiffness of outer cowl  22  is increased so that the frequency of outer cowl  22  is increased to outside a typical engine operating range. 
     FIGS. 7 and 8 illustrate outer cowl  22  with annular corrugations with outer cowl  22  being formed with a full wrap  50  (FIG. 7) or a partial wrap (FIG.  8 ). Both full wrap  50  and partial wrap  60  are located at a first end  62  of outer cowl  22 . First end  62  is the end in which the air enters the combustor  10  (see FIG.  1 ). By providing for full wrap  50  or partial wrap  60  at first end  62 , there is a smooth surface as the air enters the combustor, which provides for improved aerodynamics. While either type of wrap may be utilized with outer cowl  22 , partial wrap  60  is preferred because there is less forming of the body of outer cowl  22  to form partial wrap  60 . 
     Outer cowl  22  with annular corrugations  40  sustains the stress levels imposed thereon for a desirable number of hours without succumbing to high cycle fatigue and directs air flow to the combustor in a manner consistent with the requirements of the fuel/air mixers and the inner/outer passages. Outer cowl  22  with annular corrugations  40  is both lightweight and inexpensive in terms of materials, processing and specific fuel consumption. Moreover, by incorporating annular corrugations  40  into outer cowl  22 , the damper wire (not shown) of prior art cowls can be eliminated. Also, inner cowl  26  may also have annular corrugations  40 , which would have the same effect as on outer cowl  22 . Desired air flow into combustor  10  is typically difficult to achieve, and may be affected by any change in design for outer cowl  22 . The benefit of including corrugations into outer cowl  22  is that there is little to no impact on desired air flow into combustor  10 , including the passage pressure recoveries. 
     While this invention has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the invention. In addition, many modifications may be made to adapt a particular situation or material to the teachings of the invention without departing from the essential scope thereof. Therefore, it is intended that the invention not be limited to the particular embodiment disclosed as the best mode contemplated for carrying out this invention, but that the invention will include all embodiments falling within the scope of the appended claims.

Technology Classification (CPC): 5