Patent Grant
9328629
The present invention is related to gas turbine engines, and in particular to the outer case of a gas turbine engine.
An outer engine case for a gas turbine engine includes multiple case sections that are secured to each other at flange connections The multiple case sections are required to facilitate installation of various internal gas turbine engine components such as a compressor assembly, combustor assembly, turbine assembly, and exhaust assembly. Typically, a number of outer case assemblies are employed, with the various outer case assemblies being bolted together at flanged joints. The outer case provides structural support for the various components of the gas turbine engine which are attached thereto. However, forces applied to the outer case can result in ovalization of the case, which is detrimental to the efficiency of the engine.
An outer case employed in a gas turbine engine includes a plurality of support member bosses and a plurality of gusseted bosses. The plurality of support member bosses are disposed circumferentially around the outer case for receiving and securing support members that attach the outer case to an inner hub. The plurality of gusseted bosses are disposed circumferentially around the outer case and between the plurality of support member bosses.
Although the disclosed non-limiting embodiment depicts a turbofan gas turbine engine, it should be understood that the concepts described herein are not limited to use with turbofans as the teachings may be applied to other types of turbine engines; for example a turbine engine including a three-spool architecture in which three spools concentrically rotate about a common axis and where a low spool enables a low pressure turbine to drive a fan via a gearbox, an intermediate spool that enables an intermediate pressure turbine to drive a first compressor of the compressor section, and a high spool that enables a high pressure turbine to drive a high pressure compressor of the compressor section.
The example engine 20 generally includes low speed spool 30 and high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to outer case 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided. As discussed in more detail with respect to
Low speed spool 30 generally includes inner shaft 40 that connects fan 42 and low pressure (or first) compressor section 44 to low pressure (or first) turbine section 46. Inner shaft 40 drives fan 42 through a speed change device, such as geared architecture 48, to drive fan 42 at a lower speed than low speed spool 30. High-speed spool 32 includes outer shaft 50 that interconnects high pressure (or second) compressor section 52 and high pressure (or second) turbine section 54. Inner shaft 40 and outer shaft 50 are concentric and rotate via bearing systems 38 about engine central longitudinal axis A.
Combustor 56 is arranged between high pressure compressor 52 and high pressure turbine 54. In one example, high pressure turbine 54 includes at least two stages to provide a double stage high pressure turbine 54. In another example, high pressure turbine 54 includes only a single stage. As used herein, a “high pressure” compressor or turbine experiences a higher pressure than a corresponding “low pressure” compressor or turbine.
The example low pressure turbine 46 has a pressure ratio that is greater than about 5. The pressure ratio of the example low pressure turbine 46 is measured prior to an inlet of low pressure turbine 46 as related to the pressure measured at the outlet of low pressure turbine 46 prior to an exhaust nozzle.
Mid-turbine frame 58 of engine static structure 36 is arranged generally between high pressure turbine 54 and low pressure turbine 46. Mid-turbine frame 58 further supports bearing systems 38 in turbine section 28 as well as setting airflow entering low pressure turbine 46. As discussed in more detail with respect to
The core airflow C is compressed by low pressure compressor 44 then by high pressure compressor 52 mixed with fuel and ignited in combustor 56 to produce high speed exhaust gases that are then expanded through high pressure turbine 54 and low pressure turbine 46. Mid-turbine frame 58 includes vanes 60, which are in the core airflow path and function as an inlet guide vane for low pressure turbine 46. Utilizing vane 60 of mid-turbine frame 58 as the inlet guide vane for low pressure turbine 46 decreases the length of low pressure turbine 46 without increasing the axial length of mid-turbine frame 58. Reducing or eliminating the number of vanes in low pressure turbine 46 shortens the axial length of turbine section 28. Thus, the compactness of gas turbine engine 20 is increased and a higher power density may be achieved.
The disclosed gas turbine engine 20 in one example is a high-bypass geared aircraft engine. In a further example, gas turbine engine 20 includes a bypass ratio greater than about six (6), with an example embodiment being greater than about ten (10). The example geared architecture 48 is an epicyclical gear train, such as a planetary gear system, star gear system or other known gear system, with a gear reduction ratio of greater than about 2.3.
In one disclosed embodiment, gas turbine engine 20 includes a bypass ratio greater than about ten (10:1) and the fan diameter is significantly larger than an outer diameter of low pressure compressor 44. It should be understood, however, that the above parameters are only exemplary of one embodiment of a gas turbine engine including a geared architecture and that the present disclosure is applicable to other gas turbine engines.
Outer case 70 includes flanges 74 and 76 for connection to fore and aft case assemblies (not shown). Outer case further includes a plurality of support member bosses 78 disposed circumferentially around outer case 70 for receiving and securing support structures such as struts/rods that communicate forces from inner hub 72 to outer case 70. Additionally, a number of borescope plug/pin bosses 80 are similarly disposed circumferentially around outer case 70 that allow for insertion of a borescope for inspection of vanes 60. Although not shown in
In addition, a plurality of gusseted bosses 82 are disposed circumferentially around outer case 70, and between support member bosses 78 and/or borescope/plug bosses 80. In the embodiment shown in
The number and position of the gusseted bosses 82 act to balance stiffness provided by the main stiffness drivers such as outer case 70, inner hub 72, and the struts/rods connecting the outer case to the inner hub, with induced forces generated for example, by bearing loads, gearbox link loads, oil tank loads, and oil service tubes to provide equal system stiffness symmetry. For example, in the embodiment shown in
Each gusseted boss 82 includes flat portion 84 is approximately parallel to the engine centerline axis A, and curved portion 86 that is substantially perpendicular to flat portion 84 and engine centerline axis A. In one embodiment, the interior of gusseted boss 82 includes a hollow portion (not shown) formed by flat portion 84 and curved portion 86, which reduces the weight of outer case 70 without affecting the load bearing capability of outer case 70. In particular, the geometry of gusseted bosses 82, and the placement of bosses 82 circumferentially around outer case 70, provides additional stiffness to outer case 70 that resists or prevents ovalization of outer case 70 in response to forces applied via support member bosses 78.
In an exemplary embodiment, an outer case employed in a gas turbine engine includes a plurality of support member bosses and a plurality of gusseted bosses. The plurality of support member bosses are disposed circumferentially around the outer case for receiving and securing support members that attach the outer case to an inner hub. The plurality of gusseted bosses are disposed circumferentially around the outer case and between the plurality of support member bosses.
In one embodiment, each of the plurality of gusseted bosses may include a flat portion extending from the outer case that is substantially parallel to an engine centerline axis and a curved portion extending between the outer case and the flat portion that is substantially perpendicular to the flat portion.
In another embodiment, each of the plurality of gusseted bosses may be axially aligned with the support member bosses.
In another embodiment, the outer case may be associated with a mid-turbine frame portion of the gas turbine engine.
In another embodiment, the plurality of gusseted bosses are located to maintain system stiffness symmetry.
In another embodiment, the plurality of gusseted bosses are located circumferentially around the outer case to provide ovalization control of the outer case.
In another embodiment, seven gusseted bosses are disposed circumferentially around the outer case.
In an exemplary embodiment, a mid-turbine employed in a gas turbine engine includes an inner hub, an outer case, a plurality of vanes located in a gas path defined between the inner hub and the outer case, and a plurality of support members affixed between the inner hub and the outer case that transfer loads from the inner hub to the outer case. The outer case includes a plurality of support member bosses that receive and affix the support members to the outer case and a plurality of gusseted bosses disposed circumferentially around the outer case and between the plurality of support member bosses.
In one embodiment, the plurality of gusseted bosses may include a flat portion extending from the outer case that is substantially parallel to an engine centerline axis and a curved portion extending between the outer case and the flat portion that is substantially perpendicular to the flat portion.
In another embodiment, the plurality of gusseted bosses may be axially aligned with the support member bosses.
In another embodiment, the plurality of gusseted bosses are located to maintain system stiffness symmetry.
In another embodiment, the plurality of gusseted bosses are located circumferentially around the outer case to provide ovalization control of the outer case.
In another embodiment, seven gusseted bosses are disposed circumferentially around the outer case.
In an exemplary embodiment, a gas turbine engine includes a fan section, a compressor section located downstream from the fan section, a combustor section, a high pressure turbine section located downstream from the combustor section, a low pressure turbine section located downstream for the high pressure turbine section, and a mid-turbine frame section disposed between the high pressure turbine section and the low pressure section. The mid-turbine frame section includes an inner hub, an outer case, a plurality of vanes located in a gas path defined between the inner hub and the outer case, and a plurality of support members affixed between the inner hub and the outer case that transfer loads from the inner hub to the outer case. The outer case includes a plurality of support member bosses that receive and affix the support members to the outer case and a plurality of gusseted bosses disposed circumferentially around the outer case and between the plurality of support member bosses.
In one embodiment, the plurality of gusseted bosses may include a flat portion extending from the outer case that is substantially parallel to an engine centerline axis and a curved portion extending between the outer case and the flat portion that is substantially perpendicular to the flat portion.
In another embodiment, the plurality of gusseted bosses may be axially aligned with the support member bosses.
In another embodiment, the plurality of gusseted bosses are located to maintain system stiffness symmetry.
In another embodiment, the plurality of gusseted bosses are located circumferentially around the outer case to provide ovalization control of the outer case.
In another embodiment, seven gusseted bosses are disposed circumferentially around the outer case.
In this way, the present invention describes the use of gusseted bosses to provide ovalization control of an outer case in a gas turbine engine. 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.
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| Number | Date | Country | |
|---|---|---|---|
| 20140093368 A1 | Apr 2014 | US |
