Patent ID: 6453676
Filing Date: 2002-09-24
Classification: F23R,Y02T

Abstract:
A structure of a 50 pound thrust level turbojet engine combustor, the combustor being a through flow annular combustor type, the structure comprising:a combustor outer liner, a first series of air inlets arranged circumferentially in a dome region thereof, the first series of air inlets are spaced apart, a second series of air inlets spaced circumferentially around the outer liner to create a primary jet, a dilution jet, and a dilution enhancement jet; circular protrusions installed on a hot surface of the outer liner so as to form a film cooling means for protecting the outer liner; a round hole for receiving an ignition device being formed in a front end of the outer liner; a jet tube installed in a primary jet hole of the outer liner, the primary jet hole increases penetration depth of the primary jet in order to facilitate generation of recirculating flow in a primary zone; a combustor inner liner, a third series of air inlets arranged circumferentially around the inner liner at spaced-apart positions on the inner liner; circular protrusions are installed on a hot surface of the inner liner to form a bidirection film cooling means and a one way film cooling means for protecting the inner liner; a hub, a rear axial portion thereof being combined with the inner liner of the combustor, a circular flange being installed at an outer axial periphery thereof for combining and positioning the outer liner of the combustor; a front end of the circular flange being formed as a slope surface, the slope surface being installed with air inlets arranged circumferentially thereof; the air inlet being extended axially to be formed as a penetrating air hole; round holes circumferentially spaced and installed between the circular flange and the rear axial portion of the hub for receiving at least one atomizer; and a front portion of the hub having fuel inlets and lubricating oil inlets.