TECHNICAL FIELD
This invention relates to noise attenuating liners for fluid handling ducts such as the inlet and exhaust ducts of turbine engines.
BACKGROUND OF THE INVENTION
Turbine engines, such as those used for aircraft propulsion, include an inlet duct for delivering air to the engine and an exhaust duct for discharging combustion products to the atmosphere. During operation, the engine generates noise that propagates to the environment through the open ends of the ducts. Because the noise is objectionable, engine manufacturers install acoustic liners on portions of the interior walls of the ducts. A commonly used type of acoustic liner features an array of resonator chambers sandwiched between a perforated face sheet and an imperforate backwall. The liner is installed in the duct so that the face sheet defines a portion of the interior wall surface and is exposed to the air or combustion products flowing through the duct. Acoustic liners are designed to reduce the amplitude of the noise across a bandwidth of frequencies referred to as the design frequency band.
Acoustic liners are not completely effective. Noise at frequencies outside the design frequency band are unaffected by the liner. Even noise within the design frequency band persists, albeit at a reduced amplitude. The residual noise, whether attenuated or not, can be reflected by the liner. Some of the noise decays too rapidly with distance to propagate outside the ducts. These decay susceptible noise modes are referred to as “cut-off” modes and are not of concern. Other noise modes are decay resistant and can easily propagate long distances. These are referred to as “cut-on” modes. If a decay resistant noise signal strikes the liner at a shallow enough angle, the noise signal can reflect at a similar shallow angle and can propagate out of the duct.
One way to attenuate the cut-on modes is to regulate the direction in which the liner reflects those modes. For example, if a decay resistant noise signal strikes the liner at a shallow angle, and does so far from the open end of the duct (i.e. remote from the intake plane of an inlet duct or remote from the exhaust plane of an exhaust duct) it could be beneficial to reflect that signal at a steeper angle, i.e. in a less axial direction. The principal benefit of the steeper reflection angle is that it causes the noise signal to experience repeated reflections off the liner as the signal propagates toward the open end of the duct. This is beneficial because each interaction with the liner further attenuates the noise signal, provided the frequency of the signal is within the design frequency band of the liner. Moreover, the reflected signal decays exponentially with distance due to the inability of sound at that frequency to propagate in the duct at that angle.
It may also be beneficial to reflect a noise signal into a direction more axial than the direction of the incident signal. For example if a noise signal strikes the liner close to the open end of the duct (i.e. near the intake plane of an inlet duct or near the exhaust plane of an exhaust duct) the axial distance between the point of incidence and the open end of the duct may be too small to intercept a reflected signal, even one reflected at a steep angle. Therefore, it may be more beneficial to reflect that signal in a more axial direction. This is because noise that propagates axially from an aircraft engine spreads out over a larger area before reaching the ground than does noise that propagates nonaxially from the engine. The resulting wider distribution of the noise reduces its amplitude, making it less disturbing to observers on the ground.
One known way to regulate the angle of reflection is to employ an active backwall. An active backwall includes vibratory elements such as piezoelectric flat panel actuators. A control system responds to acoustic sensors deployed on the liner by signaling the actuators to vibrate at an amplitude and a phase angle (relative to an incident noise signal) that causes the impedance of the liner to vary with time and to do so in a way that optimizes attenuation of an incident noise signal. However such liners are not completely satisfactory because their capability is limited by the power available to drive the actuators. Moreover, the active backwall introduces unwelcome weight, cost and complexity.
In principle, an engine designer can orient the entire liner (i.e the face sheet and the backwall) so that the liner reflects incident noise signals in one or more desired directions. However doing so is almost always impractical because the interior shape of the duct is governed by aerodynamic considerations. Because the liner face sheet defines at least part of the contour of the duct interior wall, orienting the entire liner to regulate the direction of reflected noise will almost always compromise the aerodynamic performance of the duct.
What is needed is a way to redirect reflected noise in a duct without introducing undue weight, cost or complexity and without jeopardizing the aerodynamic performance of the duct.
SUMMARY OF THE INVENTION
It is, therefore, an object of the invention to redirect reflected noise in a duct without introducing undue weight, cost or complexity and without jeopardizing the aerodynamic performance of the duct.
According to one embodiment of the invention, a fluid handling duct includes an acoustic liner comprising a face sheet and a backwall laterally spaced from the face sheet. The backwall is offset from the face sheet by a nonuniform depth to direct sound waves incident upon the backwall in a prescribed direction relative to the face sheet.
In one embodiment of the invention, the backwall comprises a ramp. In another embodiment, the backwall comprises a series of steps offset from the face sheet by different depths.
The foregoing and other features of the various embodiments of the invention will become more apparent from the following description of the best mode for carrying out the invention and the accompanying drawings.
BRIEF DESCRIPTION OF THE DRAWINGS
FIG. 1 is a schematic view of a gas turbine engine inlet duct including an acoustic liner taken in the direction 1-1 of FIG. 2, i.e. looking parallel to the duct axis.
FIG. 2 is a cross sectional side elevation view in the direction 2-2 of FIG. 1.
FIG. 3 is an enlarged view of the region 3-3 of FIG. 2 showing an embodiment of the inventive acoustic liner featuring a ramped backwall.
FIG. 4 is a schematic view illustrating a definition of the relative inclinations of a face sheet and a backwall inclined more toward a noise source than the face sheet is inclined toward the noise source.
FIG. 5 is a top view looking in the direction 5-5 of FIG. 1.
FIG. 6 is an enlarged view of the region 6-6 of FIG. 5 showing an embodiment of the inventive acoustic liner featuring a ramped backwall.
FIG. 7 is a schematic view illustrating a definition of the relative inclinations of a face sheet and a backwall inclined more away from a noise source than the face sheet is inclined away from the noise source.
FIG. 8 is a view similar to FIG. 3 further enlarged and illustrating the physical behavior of the inventive acoustic liner.
FIG. 9 is a view looking parallel to the engine axis showing an acoustic liner with a backwall facing at least partly in the circumferential direction.
FIG. 10 is a cross sectional side elevation view of an embodiment of the invention in which the backwall comprises a series of steps.
FIG. 11 is a cross sectional side elevation view similar to FIG. 8 showing an embodiment of the invention with a curved backwall.
FIG. 12 is a cross sectional side elevation view similar to that of FIG. 10 showing an embodiment in which the depth of the steps follows a curved profile.
FIG. 13 is a cross sectional side elevation view showing the ramped embodiment of the invention in combination with active elements distributed along the backwall.
FIG. 14 is a schematic, cross sectional side elevation view of a turbine engine exhaust nozzle according to the invention.
BEST MODE FOR CARRYING OUT THE INVENTION
FIGS. 1, 2 and 5 illustrate a turbine engine inlet duct 20 defined by duct interior wall 22, which circumscribes a duct axis 24. The illustrated inlet duct is substantially circular in cross section when viewed parallel to the engine axis, although some inlet ducts have a noticeably less circular shape. One end 26 of the duct is open to the atmosphere. The other end of the duct, which is axially offset from the open end, is immediately forward of a compressor represented by a rotatable fan 28 having an array of blades 30. During engine operation the fan is a source of noise.
Portions of the duct interior wall 22 are lined with an acoustic liner 32. A typical acoustic liner comprises a face sheet 34 perforated by numerous small holes 36 (visible in FIGS. 3 and 6) and an imperforate back sheet or backwall 38 spaced from the face sheet. The face sheet defines the interior contour of the duct wall as seen best in FIGS. 2 and 5. An array of resonator chambers 40 or other sound attenuator occupies the space between the face sheet and the backwall. The illustrated liner is a single layer liner, however the invention is equally applicable to multiple layer liners in which one or more separating screens or perforated separating sheets resides between the face sheet and the backwall. The liner has an acoustic impedance, which is a complex quantity whose real part is referred to as resistance and whose imaginary part is referred to as reactance. The resistance, which controls the amplitude of a reflected sound wave, is set by the dissipative nature of the face sheet and any dissipative material placed within the honeycomb cells. The reactance, which controls the phase of the reflected wave, is a measure of the capacitance of the liner and is set primarily by the depth of the liner and inductive influences associated with the holes in the face sheet. The acoustic impedance may be spatially uniform, or it may be spatially nonuniform in which case the nonuniform impedance may be used to regulate the direction of reflection as described more completely in my copending, commonly owned application (Assignee's docket number EH-11451) entitled “Acoustic Liner with Nonuniform Impedance” and filed concurrently herewith, the contents of which are incorporated herein by reference.
As seen in FIGS. 3, 4, 6 and 7, the backwall 38 has a nonuniform depth D relative to the face sheet 34. Specifically, the backwall is a ramp oriented at an angle γ (γ1 in FIG. 3; γ2 in FIG. 6) relative to the face sheet. As will be described in more detail below, the orientation angle γ is selected to direct sound waves incident upon the backwall into a prescribed direction relative to the face sheet. Typically the prescribed direction is nonspecular relative to the face sheet. In FIG. 3, the backwall 38 is inclined more toward the noise source (the fan 28) than the face sheet 34 is inclined toward the noise source. As shown schematically in FIG. 4, a backwall 38 is considered to be inclined more toward a noise source 28 than the face sheet 34 is inclined toward the noise source if a first line 42 originating at an origin 44 on the backwall and extending perpendicular to the backwall crosses the duct axis 24 closer to the noise source 28 than does a second line 46 originating at the same origin 44 and extending perpendicular to the face sheet. As is evident in FIG. 4, the foregoing is true whether the face sheet and the backwall themselves are inclined toward or away from the noise source 28.
In FIG. 6, the backwall is inclined more away from the noise source (the fan 28) than the face sheet is inclined away from the noise source. As shown in schematically in FIG. 7, a backwall is considered to be inclined more away from a noise source than the face sheet is inclined away from the noise source 28 if a first line 42 originating at an origin 44 on the backwall 38 and extending perpendicular to the backwall crosses the duct axis 24 further from the noise source 28 than does a second line 46 originating at the same origin 44 and extending perpendicular to the face sheet 34. As is evident in FIG. 7, the foregoing is true whether the face sheet and the backwall themselves are inclined toward or away from the noise source 28.
Referring principally to FIGS. 2 and 3, a representative sound wave or noise signal 50 produced by the fan propagates forwardly through the inlet duct. The trajectory of the illustrated noise signal is describable by a directional component parallel to the face sheet (and therefore approximately axial) and a directional component perpendicular to the face sheet (and therefore approximately radial). The illustrated noise signal strikes the liner at an angle of incidence a and does so far from the open end 26 of the inlet duct. The backwall is oriented at angle γ1 to reflect any residue of the incident noise signal 50 in a prescribed direction as indicated by reflected signal 52 and its associated angle of reflection β. If the backwall were parallel to the face sheet, the signal would have reflected at a specular angle of reflection βs and propagated along a specular trajectory 54, i.e. a trajectory whose directional components parallel to face sheet 34 and perpendicular to face sheet 34 are equal in magnitude to the corresponding directional components of the incident signal. However, as seen in FIGS. 2 and 3, the inventive liner causes the parallel directional component of the reflected signal 52 to be lower in magnitude than the parallel directional component of the incident signal, and the perpendicular directional component of the reflected signal to be greater in magnitude than the perpendicular directional component of the incident signal. In other words the reflected trajectory is steeper than the incident trajectory. As a result, the reflected signal has more opportunities to repeatedly reflect off the liner as it propagates toward the open end of the duct, which provides repeated opportunities for the liner to attenuate the noise signal.
FIGS. 5 and 6 are similar to FIGS. 2 and 3 but show a noise signal 50 striking the liner near the open end 26 of the inlet duct. The backwall is oriented at angle γ2 to reflect any residue of the incident noise signal 50 in a prescribed direction as indicated by reflected signal 52 and its associated angle of reflection β. If the backwall were parallel to the face sheet, the signal would have reflected at a specular angle of reflection βs and propagated along a specular trajectory 54, i.e. a trajectory whose directional components parallel and perpendicular to the face sheet 34 are equal in magnitude to the corresponding directional components of the incident signal. However, as seen in FIGS. 5 and 6, the inventive liner causes the parallel directional component of the reflected signal 52 to be greater in magnitude than the parallel directional component of the incident signal, and the perpendicular directional component of the reflected signal to be lower in magnitude than the perpendicular directional component of the incident signal. In other words the reflected trajectory is shallower than the incident trajectory. As a result, the reflected signal propagates in a more axial direction and therefore is less disturbing to the surrounding community than is nonaxially propagating noise.
The prescribed direction of reflection need not be the same direction for all portions of the liner. This is evident from the foregoing examples in which portion 3-3 of the liner reflects the incident noise signal in a prescribed direction that is less axial and more radial than the incident signal whereas portion 6-6 of the liner reflects the incident signal in prescribed direction that is more axial and less radial than the incident signal.
FIG. 8 schematically illustrates the physical behavior of the inventive acoustic liner described above, disregarding a time delay that occurs when a sound wave passes through the face sheet. A sound wave represented by incident noise signal 50 approaches the liner surface at an incidence angle α. Line 130-130 represents a line of equal phase (e.g. maximum pressure crest) at time t0. At a later time, t1=t0+Δt, the wave has progressed forward by a distance s1=c(Δt) where c is the speed of propagation. The part of the pressure crest that had been closest to the liner face at time t0 has now entered the liner and has progressed toward the back wall. Thus, at time t1 the pressure crest is depicted by line 131-131. At a later time t2=t0+2Δt, the wave has progressed forward by a distance s2=c(2Δt). At time t2, part of the wave front has struck the back wall and has rebounded toward the liner face sheet. Thus, at time t2 the pressure crest is depicted by line 132-132. At time t3=t0+3Δt, the entire wave has struck the backwall and has rebounded toward the face sheet as depicted by line 133-133. At time t4=t0+4Δt, the wave has exited the liner as depicted by line 134-134. The angle β of the reflected noise signal 52 is thus seen to be equal to α+2γ. As already noted, when the backwall is inclined more toward the incident sound wave, the nonuniform depth backwall will vector the sound wave more radially (or even back towards the source for large enough inclinations). When the backwall is inclined more away from the incident sound wave the nonuniform depth backwall will vector the sound wave in a more axial direction within the duct. For the example shown in FIG. 8, the incidence angle is 45 degrees and the angle of the backwall is 22.5 degrees. Thus, the angle of reflection is 90 degrees (i.e. perpendicular to the liner face). The designer can use the relationship β=α+2γ to define the inclination of the backwall required to prescribe a desired angle of reflection β at any given location within the duct. When using the above relationship, γ is positive if the backwall is inclined more toward the noise source than the face sheet is inclined toward the noise source, and γ is negative if the backwall is inclined more away from the noise source than the face sheet is inclined away from the noise source.
The prescribed direction will ordinarily be a nonspecular direction relative to the face sheet, however some portions of the backwall may be locally oriented to achieve a specular reflection relative to the face sheet if such a direction is consistent with noise attenuation goals or if it is necessary to form a transition between portions of the backwall that each reflect nonspecularly relative to the face sheet.
The above examples show incident noise signals with both axial and radial directional components. However noise signals radiating from engine fans typically exhibit spinning modes that propagate toward the liner with a spiral motion. Such incident sound waves have a circumferential component in addition to axial and radial components. Therefore, as seen in FIG. 9, the acoustic liner may be inclined to face at least partially in the circumferential direction to redirect the reflected noise signals in the most desirable prescribed direction.
FIGS. 3, 6 and 8 show a backwall 38 in the form of a ramp, however substantially the same reflective effect may be achieved with a backwall formed as a series of steps as illustrated in FIG. 10. The illustration shows an acoustic liner whose backwall is oriented at a constant orientation angle γ relative to the face sheet as indicated by meanline 56.
Although the examples discussed herein show linear backwalls forming a constant angle γ with the face sheet, the backwall can be curved or nonlinear as seen in FIGS. 11 and 12 so that the orientation angle γ between the face sheet 34 and a line tangent to the backwall (or tangent to the meanline 56) varies with axial distance. The depth D also varies with axial distance according to a nonlinear profile.
Referring to FIG. 13, the present invention may be used in combination with an active backwall. As illustrated schematically in FIG. 13, an active backwall includes vibratory elements 64 such as piezoelectric flat panel actuators. A control system responds to acoustic sensors 62 by signaling the actuators to vibrate at an amplitude and a phase angle (relative to an incident noise signal) that causes the impedance of the liner to vary with time and to do so in a way that optimizes attenuation of an incident noise signal. The use of the variable depth backwall in combination with active elements may reduce the operational demands on the active elements leading to an accompanying reduction in the power required to drive them.
The invention, although described in the context of a turbine engine inlet duct, is equally applicable to other types of ducts, including exhaust ducts such as the fan and core engine exhaust ducts of turbine engines. As seen in the schematically illustrated exhaust duct 66 of FIG. 14, the noise source is hot, high velocity exhaust gases 68 entering upstream end 70 of the duct. The noise propagates downstream toward the open or downstream end 72 of the duct.
Although this invention has been shown and described with reference to a specific embodiment thereof, it will be understood by those skilled in the art that various changes in form and detail may be made without departing from the invention as set forth in the accompanying claims.
Patent Application
20060169533
