Gas turbine engine with seal assembly
View Patent ↗A gas turbine engine includes an interstage seal assembly positioned in a plenum between the compressor section and turbine section. The seal assembly includes an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid flow between the compressor section and the turbine section, and an annular heat shield member positioned in the plenum adjacent to the turbine section for limiting heat transfer from the turbine section to the compressor section. The annular heat shield member includes a plurality of slots formed on a surface of the heat shield member in a radial direction of the annular heat shield member.
1. A gas turbine engine comprising:
a turbine section having a turbine rotor;
a compressor section having a compressor rotor, the compressor section positioned in a proximity of the turbine section;
a plenum disposed between the turbine section and the compressor section, the plenum having first and second fluid paths adjacent to an outermost tip of the compressor rotor and the turbine rotor, respectively; and
a seal assembly positioned in the plenum, the seal assembly including:
an annular seal member positioned in the plenum adjacent to the compressor section for restraining a fluid flow between the compressor section and the turbine section via the first fluid path of the plenum; and
an annular heat shield member positioned in the plenum adjacent to the turbine section for limiting heat transfer from the turbine section to the compressor section via the second fluid path of the plenum, the annular heat shield member including a plurality of slots formed in the heat shield member.
2. The gas turbine engine of claim 1 , wherein each of the slots is disposed in a radial direction of the annular heat shield member.
3. The gas turbine engine of claim 1 , wherein the seal assembly includes an elastic member positioned between the seal member and the heat shield member to bias the heat shield member to a turbine section housing of the gas turbine engine.
4. The gas turbine engine of claim 3 , wherein the elastic member is a metal spring adapted to bias an outer end portion of the heat shield member to the turbine section housing.
5. The gas turbine engine of claim 3 , wherein the seal assembly includes a coupling member attached thereto for connecting the seal member, the heat shield member, and the elastic member together.
6. The gas turbine engine of claim 3 , wherein an outer end portion of the seal member is hermetically sealed at a compressor section housing of the gas turbine engine.
7. The gas turbine engine of claim 6 , wherein an inner end of the seal member maintains a small gap with the compressor rotor.
8. The gas turbine engine of claim 1 , wherein the heat shield member include a through hole formed in at least one end portion of each of the slots.
9. The gas turbine engine of claim 1 , wherein the heat shield member is formed of heat-resistant metal.
10. The gas turbine engine of claim 9 , wherein the heat shield member has a thickness of about 1 millimeter, and each of the slots has a width of between about 0.5 and 1 millimeter.
11. The gas turbine engine of claim 1 , wherein the gas turbine engine is a turbo charger coupled with a fuel cell system.