Power plants – Combustion products used as motive fluid
Patent
1998-04-27
1999-12-14
Casaregola, Louis A.
Power plants
Combustion products used as motive fluid
60 3908, 60 3983, F02C 714
Patent
active
060002107
DESCRIPTION:
BRIEF SUMMARY
BACKGROUND AND SUMMARY OF THE INVENTION
The invention relates to an aircraft gas turbine engine, particularly a turboprop engine, having a liquid/air heat exchanger, particularly an oil cooler, which is arranged in the engine cage and which can be acted upon by a restrictedly delivered cooling air flow which is supplied by way of an opening in the engine cage. Concerning the known state of the art, reference is made in the manner of an example to European Patent Application EP 0 514 119 A1.
It may be required to arrange air-cooled liquid heat exchangers and particularly oil coolers on aircraft gas turbine engines in such a fashion that cooling air optimally flows against these heat exchangers during the flying operation as well as during the forward rolling of the aircraft as well as during the backward rolling of the aircraft on the ground. This requirement is particularly significant in the case of turboprop engines because relatively large amounts of heat must be carried away by way of the oil coolers of these engines.
A problem, particularly during the backward rolling of the aircraft is the delivery of the air current acting upon the heat exchanger. It is therefore an object of the invention to indicate a particularly advantageous solution for this problem.
For achieving this object, it is provided that the heat exchanger is arranged in a flow duct which, on the back side, leads out into the environment and which, on the front side, can optionally be connected with an air inlet opening or with an inflow duct of the compressor of the aircraft gas turbine.
Other objects, advantages and novel features of the present invention will become apparent from the following detailed description of the invention when considered in conjunction with the accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWING
The drawing FIGURE is a schematic longitudinal partially sectional view of an aircraft gas turbine engine with a liquid-air heat exchanger according to a preferred embodiment of the present invention.
DETAILED DESCRIPTION OF THE DRAWING
Referring to the drawing, reference number 1 indicates the engine cage or engine casing of an only partially shown turboprop engine. In this engine cage which is illustrated in a partially sectional view, an aircraft gas turbine is arranged of which essentially only the compressor 2 is shown. By means of a transmission 3, the aircraft gas turbine drives a propeller 4. Because of the high power to be transmitted, the lubricating oil of the transmission 3 is heated to such an extent that an effective oil cooling must always take place. For this purpose, a liquid/air heat exchanger 5, which in the following will also be called an oil cooler 5, is arranged essentially within the engine cage 1.
This oil cooler 5 must always be acted upon by a cooling air flow. For this purpose, the oil cooler/heat exchanger 5 is arranged in a flow duct 6 which is machined into the engine cage 1. On the front side of the engine cage 1, an air inlet opening 7 is provided which can be connected with the flow duct 6. In this case, a flow guiding flap, which has the reference number 10, is in the position illustrated by a broken line. On the other side of the oil cooler 5, the flow duct 6 leads either by way of a conventional nozzle according to the arrow 16 into the environment; or by the displacement of a movable flap 15, the flow duct 6 can also be connected with the environment by way of a transfer opening 8 in the engine cage 1.
Close to the air inlet opening 7, a so-called connecting duct 9 branches off the flow duct 6, an adjustable flow guiding flap 10 being provided in the area of the branch-off. By means of an adjusting lever 12, the flow guiding flap 10 can be swivelled about a pivot 13. This flow guiding flap 10 is illustrated in its two different end positions. When the flow guiding flap 10 is in the position illustrated by a broken line, a possible connection from the flow duct 6 to the connecting duct 9 is interrupted; that is, no air transfer is possible from the flow duct 6 into the
REFERENCES:
patent: 2593541 (1952-04-01), Cowdrey et al.
patent: 2678542 (1954-05-01), Stanton
patent: 3080716 (1963-03-01), Cummings et al.
patent: 4504030 (1985-03-01), Kniat et al.
patent: 5438823 (1995-08-01), Loxley et al.
BMW Rolls Royce GmbH
Casaregola Louis A.
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