초록

An aircraft emergency power unit having a high pressure air storage tank, an aviation fuel storage tank, and a combustor which combusts pressurized air and aviation fuel in a stochiometrically fuel rich ratio to produce a motive combustion gas.

대표청구항 ▼

An aircraft emergency power unit for generating a controlled flow of motive gas to develop temporary, limited power to drive variable aircraft accessory loads in the event of an aircraft emergency, comprising: a high pressure air storage tank on the aircraft for dedicated use substantially only by s

An aircraft emergency power unit for generating a controlled flow of motive gas to develop temporary, limited power to drive variable aircraft accessory loads in the event of an aircraft emergency, comprising: a high pressure air storage tank on the aircraft for dedicated use substantially only by said emergency power unit; an aviation fuel tank for storing aviation fuel of the type which also operates the aircraft main engine, said aviation fuel tank being for dedicated use substantially only by said emergency power unit; a combustor; air cunduit means for delivering pressurized air from said air storage tank to said combustor; fuel conduit means for delivering aviation fuel from said fuel tank to said combustor; a turbine including a turbine shaft, said turbine receiving motive gas flow from said combustor inducing rotational movement thereof, said turbine shaft mechanically connected to said aircraft accessory loads; means for monitoring said aircraft accessory loads; and control means, associated with said air and fuel conduit means and said means sor monitoring, for variably adjusting the rate of flow of both the pressurized air and the aviation fuel delivered to said combustor to variably control the flow of said motive gas directed upon said turbine to adjust the power output of said turbine in response to the variable power requirements of said aircraft accessory load and for maintaining the ratio of air to aviation fuel delivered to said combustor at a fuel rich ratio in the range between about 1.5:1 to 7:1 by weight, said combustor being operable to combust the air and aviation fuel while in said fuel rich ratio, and generate therefrom said flow of motive gas at a temperature of at least about 1400°F.