发明名称 |
GAS TURBINE ENGINE MID TURBINE FRAME BEARING SUPPORT |
摘要 |
A gas turbine engine includes a fan and a compressor section that is fluidly connected to the fan. The compressor includes a high pressure compressor and a low pressure compressor. A combustor is fluidly connected to the compressor section. A turbine section is fluidly connected to the combustor. The turbine section includes a high pressure turbine coupled to the high pressure compressor via a first shaft. A low pressure turbine is coupled to the low pressure compressor via a second shaft. A geared architecture interconnects between the second shaft and the fan. The gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). The low pressure turbine has a pressure ratio that is greater than 5, and the geared architecture includes a gear reduction ratio of greater than 2.5:1. |
申请公布号 |
US2015337732(A1) |
申请公布日期 |
2015.11.26 |
申请号 |
US201514818392 |
申请日期 |
2015.08.05 |
申请人 |
United Technologies Corporation |
发明人 |
Mayer Robert Russell;Kramer George J.;Palmer Paul W. |
分类号 |
F02C7/06;F02C7/36;F02C7/20;F02C3/045 |
主分类号 |
F02C7/06 |
代理机构 |
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代理人 |
|
主权项 |
1. A gas turbine engine comprising:
high and low pressure turbines; a mid-turbine frame arranged axially between the high and low pressure turbines; a bearing operatively supported by a support structure; an inner case secured to the support structure and including a first conical member; and a bearing support to which the bearing is mounted, the bearing support including a second conical member that is secured to the first conical member at a joint, the first and second conical members arranged radially inward of the joint, the joint provided at a plane perpendicular to a rotational axis of the high and low pressure turbines, a first axial side on one side of the plane, and a second axial side on another side of the plane opposite the one side, the first and second conical members are arranged on the first axial side; a fan; a compressor section fluidly connected to the fan, the compressor comprising a high pressure compressor and a low pressure compressor; a combustor fluidly connected to the compressor section; a turbine section fluidly connected to the combustor, the turbine section comprising:
a high pressure turbine coupled to the high pressure compressor via a first shaft;a low pressure turbine coupled to the low pressure compressor via a second shaft; a geared architecture interconnects between the second shaft and the fan; and wherein the gas turbine engine is a high bypass geared aircraft engine having a bypass ratio of greater than six (6). |
地址 |
Hartford CT US |