The present invention relates to gas turbine engines, and more particularly to a turbine exhaust case of an gas turbine engine.
A “non-structural” turbine exhaust case typically used for gas turbines and is basically little more than an aerodynamic fairing, and carries no additional load other than its own weight and any aerodynamic loading effecting thereon. A “structural” turbine exhaust case on the other hand not only supports its own weight and any aerodynamic loading, but also supports a bearing housing and bearing for a main spool of the engine, typically, the low pressure spool. Present state of the art structural turbine exhaust cases, and in particular the bearing housing and the airfoils components, are made of cast components. However, cast components used in smaller airborne gas turbine engines (e.g. about 2000 lbs thrust and under) will increase the weight and thereby cost of manufacturing. Thus it would be desirable to provide a configuration with the strength-to-weight ratio.
One object of the present invention is to provide a improved structural turbine exhaust case.
In accordance with one aspect of the present invention, there is a turbine exhaust case of a gas turbine engine which comprises inner and outer case portions defining an annual gas path therebetween, the inner case portion including a bearing housing portion adapted to support a main spool bearing of the gas turbine engine, the outer case including a connection apparatus for supportably connecting the turbine exhaust case to the gas turbine engine and a plurality of sheet metal airfoils extending between the inner and outer case portions, the sheet metal airfoils structurally connecting the inner case portion to the outer case portion and supporting inner case relative to outer case.
In accordance with another aspect of the present invention, there is a turbine exhaust case of a gas turbine engine, which comprises inner and outer case portions, a bearing housing connected to and supported by the inner case portion for supporting a main spool of the gas turbine engine, a plurality of airfoils extending between the inner and outer case portions, the airfoils structurally connecting and supporting the inner case portion to the outer case portion and wherein the inner case portions are sheet metal.
In accordance with a further aspect of the present invention, there is a method provided for welding an end of a sheet metal airfoil to an annular case of a gas turbine engine, which comprises inserting the end of the airfoil into a matingly-profiled opening of the case wall and applying a weld fillet extending along an periphery of the profiled opening and fully penetrating through an entire thickness of the case wall, wherein the case wall thickness is adapted to permit said full penetration.
In accordance with a still further aspect of the present invention, there is a method provided for fabricating a turbine exhaust case of a gas turbine engine, which comprises providing inner and outer case portions with profiled openings therein, providing a bearing housing for supporting a main spool of the gas turbine engine, providing a plurality of sheet metal airfoils, and brazing the bearing housing to the inner case portion and welding the respective airfoils at opposed ends thereof to the respective inner and outer case portions, thereby structurally connecting the inner and outer case portions to bear a load of the main spool of the engine supported by the bearing housing.
In accordance with a yet further aspect of the present invention, there is a method for welding a profiled sheet metal element to a metal host having a matingly profiled opening therethrough, which comprises the step of inserting an end profiled sheet metal element into the matingly-profiled opening from a first face side of the host such that a portion of the element protrudes through the opening and extends a height above a second face side of the host and applying a weld fillet from the second face side along a periphery of the opening, wherein the protrusion height is selected so that the protruding portion is substantially consumed during the step of applying a fillet weld.
The present invention advantageously provides a structural turbine exhaust case which is lighter in weight and more reliable in operation, resulting from improved welding quality of the airfoils connected to the inner and outer case portions.
Other advantages and features of the present invention will be better understood with reference to a preferred embodiment described hereinafter.
Reference will now be made to the accompanying drawings by way of illustration showing a preferred embodiment of the present invention in which:
It will be noted that throughout the appended drawings, like features are identified by like reference numerals.
A bypass gas turbine engine seen generally in
Referring to FIGS. 1 and 2A–2B, the bypass gas turbine engine further includes a turbine exhaust case 25 which as an example of the present invention, includes an annular inner case portion 27 and an annular outer case portion 29 and a plurality of airfoils 31 circumferentially spaced apart, and radially extending between the inner and outer case portions 27, 29, thereby structurally connecting same. A bearing housing 33 is co-axially connected to the inner case portion 27 for supporting an aft end of a main shaft 35 of the low pressure spool 12. Preferably, there is a mixer 37 attached to the aft end of the outer case portion 29. A mounting flange 39 is integrated with the outer case portion 29 at the front end thereof for securing the turbine exhaust case 25 to the engine case 41 which in turn is structurally connected to the nacelle 10 through a plurality of radially extending struts 43.
In operation, combustion gases discharged from the burner 23 power the high and low pressure turbines 19 and 15, and then exhausted into the annular gas path defined between the inner and outer case portions 27, 29. The tangential components included in the exhaust gases is deswirled by the airfoils 31 of the turbine exhaust case 25, and then the exhaust gases are discharged into the atmosphere through the mixer 17 which facilitates the mixing of the exhaust gases with the bypass air flow. The bypass gas turbine engine is supported by aircraft frame, for example suspending from the wings by a mounting structure connected to the nacelle 10. Therefore, the turbine exhaust case 25 is part of the mechanical support chain for supporting the weight of the entire engine. In particular, the turbine exhaust case 25 supports a major portion of the weight of the low pressure spool 12, in addition to bearing its own weight and the aerodynamic loads affecting thereon by the exhaust gases.
In accordance with one embodiment of the present invention, at least the airfoils 31 of the turbine exhaust case 25 are made of sheet metal, preferably all components of the turbine exhaust case 25 are made from fabricating processes different from a casting process thereby avoiding porosity defects formed therein. In other words, the turbine exhaust case 25 includes no casting components; for example, sheet metal airfoils, sheet metal inner and outer case portions and machined bearing housing 33 made of a forged component. The mixer 37 is also preferably made of sheet metal fabricated in a pressing process.
The bearing housing 33 includes a cylindrical body (not indicated) defining a bore 45 machined in an accurate size for accommodating a bearing of the main shaft 35 of the low pressure spool 12. The bearing housing 33 further includes a flange portion 47 radially and upwardly extending from the cylindrical body at the aft end thereof. The flange portion 47 of the bearing housing 33 is connected by a plurality of bolts (not indicated), or alternatively by welding, to an inner support structure of the inner case portion 27 of the turbine exhaust case 25. The inner support structure of the inner case portion 27 includes a truncated conical structure 49 (more clearly seen in
Referring to
Each of the airfoils 31 is welded at opposed ends thereof to the respective inner and outer case portions 27, 29 to form the complete structure of the turbine exhaust case 25. The sheet metal mixer 37 is connected by bolts fastening the adjoining flanges (not shown) of the respective turbine exhaust case 25 and the mixer 37. However, the mixer 37 can be alternatively welded at the front end thereof to the aft end of the outer case portion 29 of the turbine exhaust case 25. In a turbine exhaust case fabrication process, the components thereof can be connected in any desired sequence, and are not limited by the above described order
Referring to
Conventionally, a welding fillet line 53 is formed at each side of the case wall 50, surrounding the sectional profile of the airfoil 31, securing the airfoil 31 to the case wall 50, as shown in
Another disadvantage of the conventional method of welding airfoil 31 to case wall 50 of the respective inner and outer case portions 27, 29 of
In accordance the present invention, the welding process is conducted only at one side of the case wall 50 out of which side of the case wall the airfoil end to be welded extends, the is, an outer side opposite to the inner side defining the annular exhaust gas path. The end of the airfoil 31 should be inserted into the opening 51 of the case wall 50 with a protruding portion H2 which is predetermined such that the protruding portion H2 of the end of airfoil 31 will be substantially consumed in weld and will not appear after the welding process.
The welding process begins with applying to the end of the airfoil 31 either a laser beam or an electron beam at the side of the case wall 50 having the protruding portion H2 of the end of the airfoil 31. The laser beam or electro-beam is adjusted to have a controlled size, resulting in the fillet 59 extending along a periphery of the profiled opening 51 of the case wall 50 and penetrating through an entire thickness of the case wall 50. Preferably, the laser beam or electron beam is further adjusted to have a controlled size such that the welding fillet 59 also penetrates through the entire thickness of the sheet metal of the airfoil 31. Therefore, the welding fillet 59 constitutes an integral and complete joining portion of the end of the airfoil 31 and the case wall 50, which eliminates any possible unwelded portions of the interface, thereby avoiding any possible cracks in the welding area. The welding process is preferably conducted with an automatic welding apparatus.
The welding method of the present invention advantageously avoids welding the airfoils to the case wall of the respective inner and outer case portions of
It should be noted that although the welding method of the present invention is described with reference to a fabricating process of welding an airfoil to the respective inner and outer case portions of the turbine exhaust case, it is applicable to use the method of the present invention for welding any other components, particularly of a gas turbine engine. For example, the bearing housing 33 which may be made of sheet metal, machined forging components or other metal components, can be welded to the inner support structure of the inner case portion 27 in accordance with the present invention.
Modifications and improvements to the above-described embodiments of the present invention may become apparent to those skilled in the art. The foregoing description is intended to be exemplary rather than limiting. The scope of the invention is therefore intended to be limited solely by the scope of the appended claims.
Number | Name | Date | Kind |
---|---|---|---|
2844001 | Alford | Jul 1958 | A |
2941781 | Boyum | Jun 1960 | A |
3156437 | Mercier | Nov 1964 | A |
3403889 | Ciokajlo | Oct 1968 | A |
3909156 | Stahl | Sep 1975 | A |
4023350 | Hovan et al. | May 1977 | A |
4117671 | Neal et al. | Oct 1978 | A |
4478551 | Honeycutt, Jr. et al. | Oct 1984 | A |
4492078 | Williamson | Jan 1985 | A |
4492518 | Neal | Jan 1985 | A |
4644129 | Miller | Feb 1987 | A |
4802821 | Krietmeier | Feb 1989 | A |
4820117 | Larrabee et al. | Apr 1989 | A |
4859143 | Larrabee et al. | Aug 1989 | A |
4920742 | Nash et al. | May 1990 | A |
4979872 | Myers et al. | Dec 1990 | A |
4989406 | Vdoviak et al. | Feb 1991 | A |
4993918 | Myers et al. | Feb 1991 | A |
5076049 | Von Benken et al. | Dec 1991 | A |
5088279 | MacGee | Feb 1992 | A |
5102298 | Kreitmeier | Apr 1992 | A |
5184459 | McAndrews | Feb 1993 | A |
5236303 | Fowler et al. | Aug 1993 | A |
5292227 | Czachor et al. | Mar 1994 | A |
5338155 | Kreitmeier | Aug 1994 | A |
5346365 | Matyscak | Sep 1994 | A |
5362204 | Matyscak et al. | Nov 1994 | A |
5634767 | Dawson | Jun 1997 | A |
5791136 | Utamura et al. | Aug 1998 | A |
5878940 | Rosenbalm | Mar 1999 | A |
5943856 | Lillibridge et al. | Aug 1999 | A |
6099165 | Tremaine | Aug 2000 | A |
6439841 | Bosel | Aug 2002 | B1 |
6739120 | Moniz et al. | May 2004 | B1 |
6792758 | Dowman | Sep 2004 | B1 |
20050022501 | Eleftheriou et al. | Feb 2005 | A1 |
20050109013 | Eleftheriou et al. | May 2005 | A1 |
20050241290 | Lapergue et al. | Nov 2005 | A1 |
Number | Date | Country |
---|---|---|
685939 | Jan 1953 | GB |
702760 | Jan 1954 | GB |
852826 | Nov 1960 | GB |
856670 | Dec 1960 | GB |
866555 | Apr 1961 | GB |
1296378 | Nov 1972 | GB |
0324699 | Dec 1997 | JP |
Number | Date | Country | |
---|---|---|---|
20060010852 A1 | Jan 2006 | US |