Variable cycle gas turbine engine

Patent · Tue Oct 18 04:00:00 EDT 1977

OSTI ID:5282740

Pedersen, G H

A variable cycle air breathing gas turbine engine includes a core engine having a combustor, a high pressure turbine stage and a low pressure stage. The high pressure stage drives a compressor for the core engine and the low pressure stage drives a bypass fan for the engine. The low pressure turbine stage includes a row of tip mounted blades located in a first bypass duct and the engine includes auxiliary inlets and crossover valve means for directing air through the first bypass duct during a first mode of engine operation to cause the tip blades on the low pressure turbine stage to operate as an auxiliary bypass fan while the primary fan is driven during the first mode to produce a bypass ratio in a second bypass duct. During a second engine operating mode crossover valve means are conditioned to communicate the first bypass duct with the primary fan and a second combustor element in the first bypass duct is operated to produce flow of motive fluid across the tip blades to drive the blades as a reaction turbine to produce a high temperature turbojet cycle of engine operation.

• Assignee: General Motors Corp.
• Patent Number(s): US 4054030
• OSTI ID: 5282740
• Country of Publication: United States
• Language: English

Related Subjects

33 ADVANCED PROPULSION SYSTEMS
330103 -- Internal Combustion Engines-- Turbine
330603* -- Vehicle Design Factors-- Engine System
AIR
BLOWERS
COMBUSTORS
COMPRESSORS
CONTROL EQUIPMENT
DESIGN
DUCTS
ENGINES
FLOW REGULATORS
FLUID FLOW
FLUIDS
GAS FLOW
GAS TURBINES
GASES
OPERATION
TURBINE BLADES
TURBINES
TURBOJET ENGINES
TURBOMACHINERY
VALVES