TANDEM ROTOR BLADES

摘要

A gas turbine engine includes a compressor section and a compressor case with a low pressure compressor (LPC) and a high pressure compressor (HPC). The HPC is aft of the LPC. The compressor case defines a centerline axis. The compressor section also includes a rotor disk defined between the compressor case and the centerline axis. A plurality of stages defined radially inward relative to the compressor case. The plurality of stages includes at least one tandem blade stage. The tandem blade stage includes a plurality of blade pairs. Each blade pair is circumferentially spaced apart from the other blade pairs, and is operatively connected to the rotor disk. Each blade pair includes a forward blade and an aft blade. The aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.

主权项

1. A turbomachine comprising:
a stator vane stage; and a tandem blade stage aft of the stator vane stage, wherein the tandem blade stage includes:
a plurality of blade pairs, each blade pair being circumferentially spaced apart from the other blade pairs, each blade pair being operatively connected to a rotor disk disposed radially inward from the blade pairs, wherein each blade pair includes a forward blade and an aft blade, wherein the aft blade is configured to further condition air flow with respect to the forward blade without an intervening stator vane stage shrouded cavity therebetween.