초록

A cooling system 46 for a turbofan gas turbine engine 10 is disclosed. Various construction details which increase the effectiveness of a heat exchanger 70, 76, 112 are disclosed. In one embodiment, a rotor shaft 98 is used to pressurize buffer air for a bearing compartment 40.

대표청구항 ▼

1. In a gas turbine engine of the type having a compressor section, a turbine section, an annular flow path for working medium gases extending through the compressor section to the turbine section, a rotor assembly and a stator assembly which bound the working medium flow path, the stator assembly b

1. In a gas turbine engine of the type having a compressor section, a turbine section, an annular flow path for working medium gases extending through the compressor section to the turbine section, a rotor assembly and a stator assembly which bound the working medium flow path, the stator assembly being spaced from the rotor assembly leaving an annular inner cavity therebetween which receives gases from the working medium flow path at a first temperature, a bearing disposed in the inner cavity which extends between the stator assembly and the rotor assembly for supporting the rotor assembly and a bearing housing which includes a casing extending circumferentially about the bearing to define a bearing compartment, the casing having at least one end adjacent the rotor assembly, the housing further including a seal means at the end which extends into proximity with the rotor assembly and a second seal means at the second end which extends into proximity with the rotor assembly, the improvement which comprises: a flow path for cooling air for the turbine section which extends through the inner cavity from the compressor section to the turbine section and which receives gases from the working medium flow path; means for creating an annular buffer cavity adjacent the seal means, the annular buffer cavity extending between the bearing compartment and the inner cavity; means for pressurizing the working medium gases at a first region of the engine; means for flowing gases from the first region of the engine to the buffer cavity adjacent the seal means, said gases in the buffer cavity having a higher static pressure than the gases in the inner cavity adjacent the buffer cavity and the bearing compartment under normal operative conditions; means for cooling said gases from the first region as the gases are flowed from the first region to the buffer cavity such that the gases are cooled to a second temperature which is less than the first temperature of the inner cavity; wherein the temperature of the gases in the buffer cavity causes the gases to have a greater autoignition time characteristic than the gases in the inner cavity adjacent the seal means. 2. The gas turbine engine as claimed in claim 1 wherein the bearing compartment is supplied with a lubricant, wherein the casing has a radially extending surface, wherein the means for flowing gases from the first region of the engine to the buffer cavity and the means for cooling said gases as the gases are flowed to the buffer cavity is a shield spaced axially from the radially extending surface of the casing leaving an annular manifold therebetween which is in flow communication with the first region of the engine and the buffer cavity and wherein the housing is adapted to transfer heat from the gases to said lubricant flowed to the bearing compartment. 3. The gas turbine engine as claimed in claim 2 wherein the means for forming an annular buffer cavity is the housing which is spaced from the rotor assembly leaving a buffer cavity therebetween. 4. The gas turbine engine as claimed in claim 3 wherein the engine further includes a means disposed in the bearing compartment for impinging lubricant on a portion of the housing adjacent to the manifold. 5. The gas turbine engine as claimed in claim 4 wherein the means for pressurizing the working medium gases is a radially extending surface on the rotor assembly which is adjacent to the gases in the inner cavity and which discharges the air into the first region. 6. The gas turbine engine as claimed in claim 5 wherein the radially extending surface is a portion of the shaft adjacent the inner cavity wherein the shaft under operative conditions is adapted to create a region of static pressure P- adjacent the seal means and a region of increased pressure P+ radially outward of said region P- and wherein the annular manifold is in flow communication with the region of increased pressure P+ and the region P-. 7. In a gas turbine engine of the type having an annular flow path for working medium gases, a rotor assembly and a stator assembly with bound the working medium flow path, the stator assembly being spaced from the rotor assembly leaving an annular inner cavity therebetween which receives gases from the working medium flow path at a first temperature, a bearing disposed in the inner cavity which extends between the stator assembly and the rotor assembly for supporting the rotor assembly and a bearing housing which includes a casing extending circumferentially about the bearing to define a bearing compartment, the casing having a first end and a second end, the housing further including a first seal means at the first end which extends into proximity with the rotor assembly and a second seal means at the second end which extends into proximity with rotor assembly, the improvement which comprises: means for pressurizing the air in the inner cavity to establish a first pressure in a first region of the inner cavity and establish a second pressure which is higher than the first pressure in a second region of the inner cavity which is radially outwardly of the first region, said means including a radially extending surface on the rotor assembly adjacent the air in the first cavity; a bearing housing which includes a casing spaced radially from the rotor assembly at the first end leaving a first annular buffer cavity therebetween adjacent the first seal means and spaced radially from the rotor assembly at the second end leaving a second annular buffer cavity therebetween adjacent the second seal means. a first shield spaced axially from the casing leaving a first annular manifold therebetween which extends radially, the manifold having a first opening in flow communication with the inner cavity and a second opening radially inwardly of the first opening which is in flow communication with the first annular buffer cavity, a second shield spaced axially from the casing leaving a second annular manifold therebetween which extends radially, the manifold having a first opening in flow communication with the inner cavity and a second opending radially inwardly of the first opening which is in flow communication with the second annular buffer cavity, an impingement plate having holes therethrough which is disposed in the first annular manifold and spaced from the casing leaving an impingement region therebetween and spaced from the first shield leaving a supply region therebetween, an impingement plate having holes therethrough which is disposed in the second annular manifold and spaced from the casing leaving an impingement region therebetween and spaced from the second shield leaving a supply region therebetween, means disposed in the bearing compartment for spraying oil on the casing adjacent the impingement region of the first manifold and the impingement region of the second manifold wherein air in the inner cavity is pressurized by rototion of the radially extending surface about the axis of rotation and air from the second region is flowed from the second region into the annular manifold and through the impingement plate, impinged on the housing, cooled and flowed to the first and second annular buffer cavities.