Rotational debris discourager for gas turbine engine bearing

#This disclosure relates to debris discourager for a gas turbine engine that prevents debris from entering a seal interface.

#A typical jet engine has multiple shafts or spools that transmit torque between turbine and compressor sections of the engine. In one example, a low speed spool generally includes a low shaft that interconnects a fan, a low pressure compressor, and a low pressure turbine. A high speed spool generally includes a high shaft that interconnects a high pressure compressor and high pressure turbine. The high and low shafts are supported for rotation relative to an engine static structure by various bearings. Carbon seals are typically utilized in each bearing compartment to provide a sealed interface between the rotating and static structures. The seals include a first seal component fixed to the static structure and a second seal component rotatable with a rotating structure. The first and second seal components cooperate to separate a wet side within the bearing compartment from a dry side external of the bearing compartment.

#Wet and dry face carbon seals are vulnerable to damage because the seals are one of the few interfaces within the gas turbine engine that have a static surface that is directly contacting a rotating surface. In order to prevent wear between these two surfaces in such a harsh environment, it is important to prevent debris from entering the sealed interface and acting like an abrasive that is ground between the components. Debris discouragers have been used near carbon seals in an attempt to prevent debris from entering the sealed interface; however, these discouragers have not always been effective.

#The disclosure can be further understood by reference to the following detailed description when considered in connection with the accompanying drawings wherein:

#FIG. 1 schematically illustrates a gas turbine engine.

#FIG. 2 is a cross-sectional view of an example of debris discourager of the gas turbine engine shown in FIG. 1.

#FIG. 1 schematically illustrates a gas turbine engine 20. The gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22, a compressor section 24, a combustor section 26 and a turbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. The fan section 22 drives air along a bypass flowpath while the compressor section 24 drives air along a core flowpath for compression and communication into the combustor section 26 then expansion through the turbine section 28. Although depicted as a turbofan gas turbine engine in the disclosed non-limiting embodiment, 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 including three-spool architectures.

#The engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38. It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided.

#The low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42, a low pressure compressor 44 and a low pressure turbine 46. The inner shaft 40 is connected to the fan 42 through a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30. The high speed spool 32 includes an outer shaft 50 that interconnects a high pressure compressor 52 and high pressure turbine 54. A combustor 56 is arranged between the high pressure compressor 52 and the high pressure turbine 54. A mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46. The mid-turbine frame 57 supports one or more bearing systems 38 in the turbine section 28. The inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A, which is collinear with their longitudinal axes.