Engine driven propulsion fan with turbochargers in series

• US 5,471,834 A
• Filed: 02/14/1994
• Issued: 12/05/1995
• Est. Priority Date: 02/14/1994
• Status: Expired due to Fees

• Current Assignee: Davorin Kapich
• Original Assignee: Davorin Kapich
• Inventors: Kapich, Davorin
• Primary Examiner(s): Bertsch, Richard A.
• Assistant Examiner(s): Wicker, William
• Application Number:
  US08/196,031
• Time in Patent Office: 659 Days
• Field of Search: 60/269, 60/611, 60/612
• US Class Current: 60/269
• CPC Class Codes: F02B 53/08 Charging, e.g. by means of rotary-piston pump
• CPC Class Codes: F02K 5/00 Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
• CPC Class Codes: Y02T 10/12 Improving ICE efficiencies

Abstract

An engine driven propulsion fan. The preferred use of this fan is to power aircraft. Two turbochargers are provided both driven in series by exhaust gasses from a rotary engine. A portion of the compressed air produced by the second turbocharger provides thrust for the engine and a portion is used for engine air, further compressed by the first turbocharger.

Claims

1. An engine driven propulsion fan system comprising:

a) a rotary Wankel engine defining an engine shaft and an exhaust for exhausting exhaust gasses,

b) a propulsion fan exhaust nozzle,

c) a fan wheel attached to said engine shaft,

d) a plurality of fan blade means attached to said fan wheel defining a propulsion fan and arranged to receive and further compress ram air, said ram air defining stage 1 compressed air, and to provide propulsion compressed air for propulsion and compressed air for combustion, said compressed air for combustion defining stage 2 compressed air,

d) a first turbocharger means for producing stage 4 compressed air for combustion, said first turbocharger means being driven by exhaust gasses from said engine and defining a first turbocharger compressed air inlet,

e) a second turbocharger means for producing stage 3 compressed air by further compressing stage 2 compressed air, said second turbocharger means being driven by exhaust gasses exhausted by said first turbocharger, said stage 3 compressed air being directed as follows;

a portion of said stage 3 compressed air being directed to the propulsion fan exhaust nozzle to provide propulsion and

a portion of said stage 3 compressed air being directed to said first turbocharger compressed air inlet.

2. An engine driven propulsion fan as in claim 1 said second turbocharger means is an axial flow turbocharger having a shaft with an axis defining an axial direction and defining a plurality of turbine blades arranged such that said exhaust gasses exit said turbine blades in essentially said axial direction.

3. An engine driven propulsion fan as in claim 1 and further comprising a bypass valve means for bypassing a portion of said exhaust around said first turbocharger and into said second turbocharger.