Patent Application
20230288162
Embodiments of the present disclosure generally relate to firearms. More specifically, embodiments of the disclosure relate to an apparatus and methods for a diverging central bore for firearm sound suppressors that improves noise and flash characteristics during firing a weapon.
Firearms, such as pistols and rifles, generally utilize expanding high-pressure gases generated by a burning propellant to expel a projectile from the weapon at a relatively high velocity. When the projectile, or bullet, exits a muzzle end of the weapon's barrel, a bright, “muzzle flash” of light and a high-pressure pulse of combustion gases accompany the bullet. The rapid pressurization and subsequent depressurization caused by the high-pressure pulse gives rise to a loud sound known as “muzzle blast,” which, like muzzle flash, can readily indicate to a remote enemy both the location of the weapon and the direction from which it is being fired. In some situations, such as covert military operations, it is highly desirable to conceal this information from the enemy by suppressing the muzzle flash and/or substantially reducing the amplitude of the muzzle blast.
The muzzle blasts of firearms may be reduced by using sound suppressors, such as “noise suppressors” and “silencers.” Suppressors generally reduce muzzle blast by reducing and controlling the energy level of propellant gases accompanying a projectile as it exits the muzzle end of the weapon. Suppressors typically comprise an elongated tubular housing containing a series of baffles that define a plurality of successive internal chambers. The internal chambers control, delay, and divert the flow, expansion, and exit of the propellant gases. The internal chambers further serve to reduce the temperature of the propellant gases so as to cause a corresponding reduction in the noise produced by the propellant gases as they ultimately exit the suppressor. A rear portion of a typical suppressor may include a mechanism for removably attaching the suppressor to a firearm, and a front portion generally includes an opening for the exit of projectiles. Further, the front portion of suppressors typically are located sufficiently forward of the muzzle end of firearms to effectively function as a muzzle flash hider.
In some embodiments, suppressors are configured to reduce the temperature and pressure of propellant gases by introducing the gases into a succession of expansion chambers so as to give rise to a controlled expansion of the gases. In other embodiments, however, suppressors may be of a “multi-stage” variety that is configured to divert a portion of the propellant gases through a plurality of radial vents to one or more un-baffled, radially disposed “blast suppressor” chambers before being introduced into the succession of expansion chambers. Although multi-stage suppressors are relatively more complex to implement, they generally provide more opportunities to delay and cool the propellant gases, and hence, to reduce muzzle blast sound levels overall.
Existing suppressors have certain drawbacks that generally hinder their operation and/or efficiency. For example, one drawback to existing suppressors is that with extended use, particulate contaminates comprising propellant gases condense and are deposited on interior surfaces, such as the surfaces of the baffles, of the suppressors. These deposits include carbon from burnt propellant, lead from projectiles, and in the case of the use of “jacketed” projectiles, copper, Teflon, and/or molybdenum disulfide. While these deposits can usually be cleaned away with suitable solvents, they are typically hard and adhesive in nature, making it difficult or impossible to effectively clean the suppressor without damaging its parts.
A drawback to existing suppressors is that conventional sound and flash suppression generally causes higher back pressures within the suppressors. Higher back pressure is known to expose an operator of a weapon to toxic fumes arising due to firing the weapon. As such, a potential risk to the health of the operator grows in direct proportion to the amount of time spent using the weapon.
A drawback to existing multi-stage suppressors is that the blast suppressor chambers generally experience substantially greater radial pressures and temperatures than the succession of baffled expansion chambers. The difference in pressure and temperature does not ordinarily present a problem during intermittent firing of a weapon, wherein sufficient time passes between rounds to allow the pressure and temperature within the suppressor to abate. During a relatively high rate of fire, such as sustained fully automatic fire, the difference in pressure and temperature may cause the outer tubular housing of the suppressor to fail prematurely. In some instances, the outer tubular housing may “blow out” due to sustained local pressures and temperatures during fully automatic firing of the weapon.
Still another problem with existing suppressors pertains to their ability to effectively suppress muzzle flash. Many existing suppressors are known to exhibit a relatively large muzzle flash when a first round is fired through the suppressor, such as when the weapon has not been recently fired. Immediately subsequent rounds, however, typically do not exhibit this relatively large muzzle flash.
Still another problem with existing suppressors pertains to their ability to effectively suppress muzzle flash at high temperatures. Many existing suppressors with good first and steady state flash performance are known to exhibit a large, intermittent muzzle flash when the suppressor reaches a threshold temperature due to successive firings.
Given the above-mentioned drawbacks to existing suppressors, there is a continuous desire to develop firearm sound suppressors that exhibit relatively low back pressure while effectively suppressing sound and flash due to firing the weapon.
An apparatus and methods are provided for a front plate having a diverging central bore for firearm sound suppressors that improves noise and flash characteristics during firing a weapon. The central bore is disposed between a back surface and a front surface of the front plate. An untapered portion of the central bore extends from the back surface to a diverging portion that opens toward the front surface. The diverging portion includes a curvature profile configured to allow for more controlled expansion of high-pressure propellant gases exiting of the suppressor through the central bore. The curvature profile provides an included angle of the central bore that decreases secondary flash events accompanying the expulsion of propellant gases accompanying a fired bullet exiting the suppressor through the central bore. The curvature profile exhibits a cross-sectional area of the central bore that is proportional to a distance along the diverging portion.
In an exemplary embodiment, a front plate for a suppressor for coupling with a muzzle end of a barrel of a firearm for reducing muzzle blast and eliminating muzzle flash comprises: a central bore disposed between a back surface and a front surface of the front plate; and an untapered portion of the central bore extending from the back surface to a diverging portion.
In another exemplary embodiment, a front-most portion of the central bore is substantially flush with the front surface of the front plate. In another exemplary embodiment, the diverging portion opens toward the front surface of the front plate and has an included angle. In another exemplary embodiment, the included angle ranges between approximately 10 degrees and approximately 25 degrees.
In another exemplary embodiment, at least one recess is disposed between an outer rim and the central bore of the front plate. In another exemplary embodiment, one or more scallops are disposed in the at least one recess and arranged around the central bore. In another exemplary embodiment, the diverging portion includes a contoured or parabolic shape configured to allow for a more controlled expansion of high-pressure propellant gases exiting of the suppressor through the central bore. In another exemplary embodiment, the contoured or parabolic shape is configured to reduce turbulent properties of the high-pressure propellant gases.
In another exemplary embodiment, the diverging portion includes a curvature profile comprising a straight line extending between a first point of the diverging portion and a second point of the diverging portion. In another exemplary embodiment, the curvature profile is configured to provide a cross-sectional area of the central bore that is directly proportional to a position along the curvature profile between the first point and the second point. In another exemplary embodiment, the curvature profile is configured to provide a cross-sectional area of the central bore that increases as a function of the distance from the first point. In another exemplary embodiment, the curvature profile comprises a curved segment that resembles a portion of a parabola. In another exemplary embodiment, the curvature profile is configured to provide an included angle of the central bore that decreases secondary flash events accompanying the expulsion of propellant gases accompanying a fired bullet exiting the suppressor by way of the central bore.
In an exemplary embodiment, a method for configuring a diverging central bore for a suppressor for coupling with a muzzle end of a barrel of a firearm for reducing muzzle blast and eliminating muzzle flash comprises: providing a diameter of an untapered portion of the diverging central bore; specifying a desired bore diameter at a distance along a diverging portion of the diverging central bore; computing a slope area curve by way of the desired bore diameter; determining a cross-sectional area of the diverging portion as a function of distance along the diverging portion; and configuring a curvature profile of the diverging portion.
In an exemplary embodiment, a suppressor for coupling with a muzzle end of a barrel of a firearm for reducing muzzle blast and eliminating muzzle flash comprises: a housing having a proximal end and a distal end; a front portion within the housing for attenuating the temperature and energy of propellant gases; an annular gas expansion chamber for directing a portion of the propellant gases to peripheral vents disposed at the distal end; a rear portion for deflecting and rebounding a portion of the propellant gases before entering the annular gas expansion chamber; and a front plate including a diverging central bore adapted to provide an exit to a projectile fired from the firearm.
In another exemplary embodiment, the diverging central bore includes a curvature profile comprising a straight line extending between a first point of the diverging central bore and a second point of the diverging central bore. In another exemplary embodiment, the curvature profile is configured to provide a cross-sectional area of the diverging central bore that is directly proportional to a position along the curvature profile between the first point and the second point. In another exemplary embodiment, the curvature profile is configured to provide a cross-sectional area of the diverging central bore that increases as a function of the distance from the first point. In another exemplary embodiment, the curvature profile comprises a curved segment that resembles a portion of a parabola. In another exemplary embodiment, the curvature profile is configured to provide an included angle of the diverging central bore that decreases secondary flash events accompanying the expulsion of propellant gases accompanying a fired bullet exiting the suppressor by way of the central bore.
In an exemplary embodiment, a front plate for a suppressor for coupling with a muzzle end of a barrel of a firearm for reducing muzzle blast and eliminating muzzle flash comprises: a central bore disposed between a back surface and a front surface of the front plate; a converging portion of the central bore extending from the back surface; and a diverging portion of the central bore opening toward the front surface.
In another exemplary embodiment, the converging portion meets the diverging portion within an interior of the central bore. In another exemplary embodiment, the converging portion comprises a smooth surface beginning at a start angle with respect to the back surface. In another exemplary embodiment, the converging portion meets the diverging portion at a location within the central bore having a tangent angle with respect to a longitudinal axis of the central bore. In another exemplary embodiment, the tangent angle comprises an end angle of the converging portion and comprises a start angle of the diverging portion. In another exemplary embodiment, the converging portion smoothly blends with the diverging portion so as to maintain an attachment of the propellant gasses to walls of the central bore along the length of the central bore.
In another exemplary embodiment, the converging portion blends joins the diverging portion with a non-tangent blend, such that the expansion of the supersonic gasses is controlled. In another exemplary embodiment, the converging portion and the diverging portion are discontinuous, such that control of the expansion of the supersonic gasses is controlled. In another exemplary embodiment, the converging portion and the diverging portion comprise a combination of multiple straight and/or curved profiles, such that the resulting profile is functionally equivalent to embodiments wherein the end angle of the converging portion comprises the start angle of the diverging portion. In another exemplary embodiment, the converging portion smoothly blends with the diverging portion so as to maintain an attachment of the propellant gasses to walls of the central bore along the length of the central bore. In another exemplary embodiment, the performance of the front plate may be tuned to certain ambient conditions by manipulating the geometry of any one or more of the converging portion, the diverging portion, the start angle, the end angle, and the overall length of the central bore.
In another exemplary embodiment, the converging portion extends from a backmost surface of the front plate and meets the diverging portion within an interior of the central bore. In another exemplary embodiment, the converging portion extends from a point inset from a backmost surface of the front plate and meets the diverging portion within an interior of the central bore. In another exemplary embodiment, the converging portion comprises a straight bore. In another exemplary embodiment, the backmost surface is disposed proximal of the back surface by an offset distance. In another exemplary embodiment, the offset distance gives the central bore an overall nozzle length that is greater than the distance between the back surface and the front surface of the front plate. In another exemplary embodiment, the converging portion comprises a throat area of the central bore at the backmost surface.
In another exemplary embodiment, the diverging portion comprises an exit area of the central bore at the front surface. In another exemplary embodiment, desirable expansion, speed, and/or turbulence properties of the propellant gases transiting the central bore can be obtained by manipulating any one or more of the throat area, the exit area, a ratio of throat area to exit area, the offset distance, the overall nozzle length, or any combination thereof. In another exemplary embodiment, the throat area and the exit area may be configured to produce a desired ratio between a mass flux of the propellant gases transiting the central bore and the mass flux of the propellant gases exiting an annular exit area comprising peripheral vents surrounding the front plate. In another exemplary embodiment, the throat area and the exit area are configured to produce a desired ratio between a mass flux of the propellant gases transiting the central bore and the mass flux of the propellant gases exiting an annular exit area comprising a plurality of peripheral vents surrounding the central bore.
In an exemplary embodiment, a suppressor for coupling with a muzzle end of a barrel of a firearm for reducing muzzle blast and eliminating muzzle flash comprises: a housing having a proximal end and a distal end; a front portion within the housing for attenuating the temperature and energy of propellant gases; an annular gas expansion chamber for directing a first portion of the propellant gases to peripheral vents disposed at the distal end; and a central bore for directing a second portion of the propellant gases out of the front portion.
In another exemplary embodiment, the central bore is configured to produce a desirable ratio between a mass flux of the first portion and the mass flux of the second portion. In another exemplary embodiment, the central bore is configured to produce a desirable ratio between a gas speed of the first portion and the gas speed of the second portion. In another exemplary embodiment, the central bore is configured to produce a desirable interaction between gas flow of the first portion and gas flow of the second portion. In another exemplary embodiment, the central bore includes a converging portion that smoothly blends with a diverging portion that opens to a front of the front portion. In another exemplary embodiment, the converging portion and the diverging portion are configured to maintain an attachment of the propellant gasses to interior walls of the central bore along a length of the central bore.
In another exemplary embodiment, the converging portion blends joins the diverging portion with a non-tangent blend, such that the expansion of the supersonic gasses is controlled. In another exemplary embodiment, the converging portion and the diverging portion are discontinuous, such that control of the expansion of the supersonic gasses is controlled. In another exemplary embodiment, the converging portion and the diverging portion comprise a combination of multiple straight and/or curved profiles, such that the resulting profile is functionally equivalent to embodiments wherein the end angle of the converging portion comprises the start angle of the diverging portion. In another exemplary embodiment, the converging portion smoothly blends with the diverging portion so as to maintain an attachment of the propellant gasses to walls of the central bore along the length of the central bore. In another exemplary embodiment, the converging portion extends from a point inset from a backmost surface of the front plate and meets the diverging portion within an interior of the central bore. In another exemplary embodiment, the converging portion comprises a straight bore.
In another exemplary embodiment, performance of the front plate may be tuned to certain ambient conditions by manipulating the geometry of either or both of the converging portion and the diverging portion. In another exemplary embodiment, expansion, speed, and/or turbulence properties of the propellant gases can be optimized by manipulating any one or more of a throat area of the converging portion, an exit area of the diverging area, a ratio of the throat area to the exit area, an offset distance between the throat area and a back surface of the front plate, an overall nozzle length of the central bore, or any combination thereof.
These and other features of the concepts provided herein may be better understood with reference to the drawings, description, and appended claims.
The drawings refer to embodiments of the present disclosure in which:
While the present disclosure is subject to various modifications and alternative forms, specific embodiments thereof have been shown by way of example in the drawings and will herein be described in detail. The present disclosure should be understood to not be limited to the particular forms disclosed, but on the contrary, the intention is to cover all modifications, equivalents, and alternatives falling within the spirit and scope of the present disclosure.
In the following description, numerous specific details are set forth in order to provide a thorough understanding of the present disclosure. It will be apparent, however, to one of ordinary skill in the art that the diverging central bore and methods disclosed herein may be practiced without these specific details. In other instances, specific numeric references such as “first chamber,” may be made. However, the specific numeric reference should not be interpreted as a literal sequential order but rather interpreted that the “first chamber” is different than a “second chamber.” Thus, the specific details set forth are merely exemplary. The specific details may be varied from and still be contemplated to be within the spirit and scope of the present disclosure. The term “coupled” is defined as meaning connected either directly to the component or indirectly to the component through another component. Further, as used herein, the terms “about,” “approximately,” or “substantially” for any numerical values or ranges indicate a suitable dimensional tolerance that allows the part or collection of components to function for its intended purpose as described herein.
In general, muzzle blasts of firearms may be reduced by using sound suppressors, such as “noise suppressors” and “silencers.” Existing suppressors have certain drawbacks that generally hinder their operation and/or efficiency. One drawback to existing suppressors is that many existing suppressors exhibit a relatively large muzzle flash when a first round is fired through the suppressor, such as when the weapon has not been recently fired, while subsequent rounds typically do not exhibit this relatively large muzzle flash. Embodiments presented herein provide a diverging central bore to be implemented in suppressors to effectively minimize muzzle flash and muzzle blast.
The suppressor 100 illustrated in
As described in detail in U.S. Pat. No. 8,505,680, which is incorporated herein by reference in its entirety, it is common for a first round fired from a “cold” conventional suppressor (e.g., a suppressor that has not been recently fired) to exhibit a relatively large muzzle flash, while immediately succeeding rounds fired through the same suppressor typically do not exhibit as large a flash as that exhibited by the first round.
Experimental observation has demonstrated that this transient phenomenon results from circumstances where a suppressor through which a round has not recently been fired is relatively “cool” and is filled with oxygen-rich ambient air. As such, the cold suppressor may be substantially at thermal equilibrium with its surrounding environment and its interior lumens and chambers may be substantially filled with ambient air rather than combustion gases. When an initial round is then fired through the suppressor, the oxygen content of the gas within the suppressor is sufficient to sustain additional combustion of the oxygen within the suppressor, giving rise to a relatively large flash at an outlet end thereof. When subsequent rounds are fired through the suppressor, however, the oxygen content of the gas in the suppressor is relatively depleted due to the interior lumens and chambers having become substantially filled with combustion gases. Thus, additional combustion of oxygen within the suppressor is no longer sustainable, and relatively smaller muzzle flashes are produced.
Experimental observation has further shown that the heightened first-round muzzle flash phenomenon discussed above can be substantially reduced or eliminated altogether by providing a suppressor, such as the suppressor 100, with a front plate 128 having a central bore 132 (e.g., a frusto-conical bore in one embodiment) extending therethrough and including a taper. The taper has been observed to reduce the size of the first-round muzzle flash by permitting additional ambient air to escape from within the suppressor 100 prior to combustion of the associated oxygen. It is contemplated that the ambient air escaping the central bore 132 distributes the first-round muzzle flash and at least some associated gases over a broader area, thus reducing the length of the first-round muzzle flash. Such an implementation can reduce the size and/or length of the first-round muzzle flash and is particularly useful to reduce the detection (e.g., visual, thermal, and/or infrared imaging) of automatic weapons fired from hidden or obscured locations.
As further shown in
It is contemplated that any of various scallops and recesses may be provided in the front plate 180 to reduce weight. For example, a recess 212 may be disposed between an outer rim or lip of the front plate 180 and a central portion of the front plate 180 providing the central bore 184. As will be appreciated, scallops (not shown) can be disposed in the recess 212 and arranged around the central bore 184 to enhance the aesthetic appeal of the front plate 180 as well as to reduce weight. Further, in the particular example embodiment illustrated in
As described herein, the tapered portion 188 of the central bore 184 has been observed to reduce the size of the first-round muzzle flash by permitting additional ambient air to escape from within the suppressor 100 prior to combustion of the associated oxygen. It is contemplated that the ambient air escaping the central bore 184 distributes the first-round muzzle flash and at least some associated gases over a broader area, thus reducing the length of the first-round muzzle flash. Such an implementation can reduce the size and/or length of the first-round muzzle flash and is particularly useful to reduce the detection (e.g., visual, thermal, and/or infrared imaging) of automatic weapons fired from hidden or obscured locations.
Moreover, it is contemplated that the tapered portion 188 has at least a contoured or parabolic shape that may allow for a more controlled expansion of high-pressure propellant gases that leave the distal end 124 of the suppressor 100 through the central bore 184. Additionally, the contoured or parabolic shape of the tapered portion 188 may reduce the strength of the oblique shock train originating at the central bore exit 220 and improve flash characteristics. Further, the contoured or parabolic shape of the tapered portion 188 contributes to turning the edges of the high-pressure propellant expelled gases parallel with the direction of primary flow, which will greatly decrease larger turbulent structures at the boundaries of the suppressor 100. The decrease in turbulent properties exiting the central bore 184 enables decreasing secondary flash events that accompany the expulsion of propellant gases accompanying a fired bullet exiting the suppressor by way of the central bore 184.
Moreover, the degree of taper comprising the diverging portion 232 may be varied to optimize the decrease in turbulent properties exiting the central bore 224. For example, in the embodiment shown in
In some embodiments, however, the curvature profile 240 may comprise a curved segment, such as a portion of a parabola, or other suitable function, without limitation. For example, in one embodiment, the curvature profile 240 may be configured such that the cross-sectional area of the central bore 224 increases in direct proportion to the square of the distance from the first point 244. In another embodiment, the curvature profile 240 may be configured such that the cross-sectional area of the central bore 224 increases as a function of the cube of the distance from the first point 244. Other functions are contemplated, without limitation. Further, the curvature profile 240 may be configured to produce any of various included angles 236 as are found to be beneficial for decreasing secondary flash events accompanying the expulsion of propellant gases accompanying a fired bullet exiting the suppressor 100 by way of the central bore 224.
As will be recognized by those skilled in the art, the Area Equation 260 is a linear expression having a slope comprising a Slope Area Curve 264. The Slope Area Curve 264 is computed by way of a desired bore diameter 268 that may be specified for a particular distance along the diverging portion 232. For example, in the exemplary embodiment of
Once the Slope Area Curve 264 is determined, the Area Equation 260 may be used to compute a series of cross-sectional area values 272 and corresponding diameter values 276 based on a series of distance values 280 along the diverging portion 232. As will be appreciated, the variation in the cross-sectional area values 272 and diameter values 276, taken as a function of distance, dictate the specific configuration of the curvature profile 240 along the diverging portion 232 as well as the value of the included angle 236. As such, each of the tables shown in
In the illustrated embodiment of
In some embodiments, the converging portion 292 blends joins the diverging portion 296 with a non-tangent blend, such that the expansion of the supersonic gasses is controlled. In some embodiments, the converging and diverging portions 292, 296 are discontinuous, such that control of the expansion of the supersonic gasses is still controlled. Further, in some embodiments, the converging and diverging portions 292, 296 may comprise an advantageous combination of multiple straight and/or curved profiles, such that the resulting profile is functionally equivalent to embodiments wherein the end angle 312 of the converging portion 292 comprises the start angle of the diverging portion 296.
As further shown in
While the diverging central bore and methods have been described in terms of particular variations and illustrative figures, those of ordinary skill in the art will recognize that the diverging central bore is not limited to the variations or figures described. In addition, where methods and steps described above indicate certain events occurring in certain order, those of ordinary skill in the art will recognize that the ordering of certain steps may be modified and that such modifications are in accordance with the variations of the diverging central bore. Additionally, certain of the steps may be performed concurrently in a parallel process when possible, as well as performed sequentially as described above. To the extent there are variations of the diverging central bore, which are within the spirit of the disclosure or equivalent to the diverging central bore found in the claims, it is the intent that this patent will cover those variations as well. Therefore, the present disclosure is to be understood as not limited by the specific embodiments described herein, but only by scope of the appended claims.
This application is a continuation-in-part of, and claims the benefit of, U.S. patent application, entitled “Firearm Sound Suppressor With Peripheral Venting,” filed on Aug. 5, 2022, and having application Ser. No. 17/882,430, which claims the benefit of, and priority to, U.S. Provisional Application, filed on Aug. 6, 2021, and having application Ser. No. 63/230,515, the entirety of each of said applications being incorporated herein by reference.
| Number | Date | Country | |
|---|---|---|---|
| 63230515 | Aug 2021 | US |
| Number | Date | Country | |
|---|---|---|---|
| Parent | 17882430 | Aug 2022 | US |
| Child | 17990593 | US |
