Patent Application
20090064684
1. Technical Field
The disclosure generally relates to gas turbine engines.
2. Description of the Related Art
Modern gas turbine engines typically incorporate an Electronic Engine Control (EEC), also referred to as a Full Authority Digital Engine Control (FADEC), for controlling engine functions. In this regard, an EEC functions as a primary interface between the gas turbine engine and an aircraft to which the engine is attached. By way of example, an EEC can receive thrust commands from thrust lever resolvers and can alter operating parameters of the engine responsive to those thrust commands.
Oftentimes, an EEC is configured as a line replaceable unit (LRU) that can be removed from an aircraft and replaced by ground maintenance personnel. Access to an EEC, such as for removal and replacement, typically is provided by an access panel that is located on the engine nacelle. Notably, such an EEC typically is mounted to the engine fan case aft of a fan blade containment zone for turbofan engines.
Systems involving inlet-mounted engine control components are provided. In this regard, an exemplary embodiment of such a system comprises: a forward keep out zone defined by converging inner and outer walls of a nacelle; an aft keep out zone defined by a containment zone; and an engine control component, at least a portion of which is located between the forward keep out zone and the aft keep out zone, and between the inner and outer walls of the nacelle.
Another embodiment of such a system comprises: a nacelle having an inlet, the inlet defining a gas flow path for intake air of a gas turbine engine, the inlet further defining an annular volume about the gas flow path; and an engine control component, at least a portion of which is located within the annular volume defined by the inlet.
Still another embodiment comprises: a gas turbine engine having a fan operative to provide thrust; and an engine control component located forward of the fan.
Other systems, methods, features and/or advantages of this disclosure will be or may become apparent to one with skill in the art upon examination of the following drawings and detailed description. It is intended that all such additional systems, methods, features and/or advantages be included within this description and be within the scope of the present disclosure.
Many aspects of the disclosure can be better understood with reference to the following drawings. The components in the drawings are not necessarily to scale. Moreover, in the drawings, like reference numerals designate corresponding parts throughout the several views.
Systems involving inlet-mounted engine controls are provided. In this regard, several embodiments will be described in which a component involved in engine control, e.g., an Electronic Engine Control (EEC), is mounted within an inlet portion of a nacelle that is used to mount a gas turbine engine. In some embodiments, as least a portion of the engine control component is mounted forward of a fan containment zone of the gas turbine engine.
Reference is now made to the schematic diagram of
An embodiment of a system involving an inlet-mounted engine control is depicted schematically in
Nacelle 102 includes an inlet 112 for the gas turbine engine. Specifically, the inlet incorporates an inner (radially-innermost) wall 114, which defines a gas flow path 116 to the gas turbine engine, and an outer (radially-outermost) wall 118, which defines an exterior of nacelle. A cavity 120, which defines an annular volume about the gas flow path, is formed between the inner wall 114 and the outer wall 118.
In the embodiment of
Various mounting techniques, such as those involving brackets, can be used to mount the component to the fan case. In other embodiments, an engine control component could be mounted within an inlet cavity without being attached to the fan case.
Placement of an engine control component in an inlet may tend to reduce vibrations experienced by the engine control component. This is because the inlet is more distant from the source of vibration of the gas turbine engine than conventional mounting locations, which are located aft of the fan containment zone. Additionally, availability of unoccupied volume of the inlet may improve cable routing considerations, for example.
In this regard, a prior art cable-routing configuration is depicted schematically in
In contrast, another embodiment of a system involving an inlet-mounted engine control component is depicted schematically in
Mounting of an engine control component, e.g., EEC 160, within volume 152 may make it possible to use straight electrical connectors. For example, cable 162 is connected to the EEC 160 by a straight connector 164. This configuration is possible due to the increased available volume for mounting the component with cable runs that exhibit increased bend radii RB. Such cable runs may be more durable than cable runs that use angled connectors, as angled connectors tend to impose more stress on the cables.
It should be emphasized that the above-described embodiments are merely possible examples of implementations set forth for a clear understanding of the principles of this disclosure. Many variations and modifications may be made to the above-described embodiments without departing substantially from the spirit and principles of the disclosure. By way of example, although the above-described embodiments involve the use of turbofan engines, other types of gas turbine engines could be used. All such modifications and variations are intended to be included herein within the scope of this disclosure and protected by the accompanying claims.
