公开(公告)号：US20240141834A1

公开(公告)日：2024-05-02

申请号：US18148559

申请日：2022-12-30

Applicant: General Electric Company

Inventor： Vaishnav Raghuvaran ,  Sesha Subramanian ,  Hari Krishna Meka ,  Vishnu Vardhan Venkata Tatiparthi ,  Raghuveer Chinta ,  Daniel O'Brien ,  Sai Raju Ippili ,  Michael Thomas Hogan

IPC: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F02C7/28

CPC classification number: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/201

Abstract: A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.

公开(公告)号：US12044172B2

公开(公告)日：2024-07-23

申请号：US18148559

申请日：2022-12-30

Applicant: General Electric Company

Inventor： Vaishnav Raghuvaran ,  Sesha Subramanian ,  Hari Krishna Meka ,  Vishnu Vardhan Venkata Tatiparthi ,  Raghuveer Chinta ,  Daniel O'Brien ,  Sai Raju Ippili ,  Michael Thomas Hogan

IPC: F01D25/12 ,  F01D25/14 ,  F02C7/18 ,  F02C7/28

CPC classification number: F02C7/18 ,  F01D25/12 ,  F01D25/14 ,  F02C7/28 ,  F05D2220/32 ,  F05D2240/55 ,  F05D2260/201

Abstract: A gas turbine engine that defines a radial direction and axial direction. The gas turbine engine includes a compressor section that includes a high pressure compressor. The high pressure compressor includes an aft-most compressor stage. The aft-most compressor stage includes a rotor, a low pressure shaft, a high pressure shaft drivingly coupled to the high pressure compressor. The high pressure shaft includes a central spool member and a forward spool member. The forward spool member extending between the central spool member and the aft-most compressor stage. The aft-most compressor stage further includes an air guide coupled to the aft-most compressor stage and the high pressure shaft. The air guide and a radially inward side of the forward spool member together defines an air flow passage for providing a cooling air flow.