US 11,834,953 B2
Seal assembly in a gas turbine engine
Krishna Chaitanya Veluru, Jupiter, FL (US); Amit K. Paspulati, Charlotte, NC (US); Dimitri Zelmer, Oberhausen (DE); and Anil L. Salunkhe, Charlotte, NC (US)
Assigned to Siemens Energy Global GmbH & Co. KG, Munich (DE)
Appl. No. 17/597,127
Filed by Siemens Energy Global GmbH & Co. KG, Munich (DE)
PCT Filed Apr. 24, 2020, PCT No. PCT/US2020/029673
§ 371(c)(1), (2) Date Dec. 27, 2021,
PCT Pub. No. WO2020/263395, PCT Pub. Date Dec. 30, 2020.
Claims priority of provisional application 62/867,994, filed on Jun. 28, 2019.
Prior Publication US 2022/0228501 A1, Jul. 21, 2022
Int. Cl. F01D 11/00 (2006.01); F04D 29/08 (2006.01); F04D 29/54 (2006.01); F16J 15/3288 (2016.01)
CPC F01D 11/00 (2013.01) [F04D 29/083 (2013.01); F04D 29/541 (2013.01); F16J 15/3288 (2013.01); F05D 2220/32 (2013.01); F05D 2240/56 (2013.01)] 8 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a compressor section comprising an outlet guide vane assembly;
a mid-frame section arranged downstream of the compressor section, wherein the mid-frame section comprises an inner compressor exit diffuser, wherein the outlet guide vane assembly interfaces with a forward side of the inner compressor exit diffuser;
a turbine section arranged downstream of the mid-frame section; and
a seal assembly arranged at the forward side of the inner compressor exit diffusor,
wherein the seal assembly is radially arranged between the outlet guide vane assembly and the forward side of the inner compressor exit diffusor,
wherein the seal assembly comprises a plurality of brush seals arranged tandem along an axial direction, wherein at least one of the plurality of brush seals is mounted in the inner compressor exit diffusor and radially engages the outlet guide vane assembly, and wherein at least another one of the plurality of brush seals is mounted in the outlet guide vane assembly and radially engages the inner compressor exit diffusor.