阅读说明：本技术 喷射噪声抑制器 (Jet noise suppressor ) 是由 H·沈 M·T·拉克布林克 T·M·加勒特 于 2019-06-21 设计创作，主要内容包括：本发明的名称是喷射噪声抑制器。提供了喷射噪声抑制器和飞机。喷射噪声抑制器包括具有前端(222)、后端(224)、内表面(226)和外表面(228)、多个支柱(230)和多个通风口(240)的喷嘴。每个支柱(230)包括基部(232)和远端(234),每个支柱(230)的基部(232)连接到喷嘴的内表面,并且每个通风口(240)对应于相应支柱(230),并且形成在喷嘴的前端和相应支柱(230)的基部之间的喷嘴的内表面内。(The invention provides an injection noise suppressor. Provided are a jet noise suppressor and an aircraft. The jet noise suppressor includes a nozzle having a front end (222), a rear end (224), an inner surface (226), and an outer surface (228), a plurality of struts (230), and a plurality of vents (240). Each strut (230) includes a base (232) and a distal end (234), the base (232) of each strut (230) being connected to the inner surface of the nozzle, and each vent (240) corresponds to a respective strut (230) and is formed in the inner surface of the nozzle between the front end of the nozzle and the base of the respective strut (230).)

1. An injection noise suppressor (200) comprising:

a nozzle (120, 220) including a forward end (222), a rearward end (224), an inner surface (226), and an outer surface (228);

a plurality of struts (230), each strut (230) comprising a base (232) and a distal end (234), the base (232) of each strut (230) connected to the inner surface (226) of the nozzle (120, 220); and

a plurality of vents (240), each vent (240) corresponding to a respective strut (230) and formed within the inner surface (226) of the nozzle (120, 220) between the front end (222) of the nozzle (220) and the base (232) of the respective strut (230).

2. The jet noise suppressor (200) of claim 1, wherein each vent (240) extends from the base (232) of the respective strut (230) through the respective strut (230) to the distal end (234) of the respective strut (230).

3. The jet noise suppressor (200) of claim 2, wherein:

each vent (240) includes an inlet (242) and an outlet (244);

the inlet (242) of each vent (240) is formed within the inner surface (226) of the nozzle (220) between the front end (222) of the nozzle (220) and the base (232) of the respective strut (230); and

the outlet (244) of each vent (240) is formed within the distal end (234) of the respective strut (230).

4. The jet noise suppressor (200) of claim 3 wherein the inlet (242) of each vent (240) is formed near the front end (222) of the nozzle (220) or within the front end (222) of the nozzle (220).

5. The jet noise suppressor (200) of claim 1 wherein the distal end (234) of each strut (230) is free-standing such that each strut (230) is directly or indirectly connected to the nozzle (220) only at the base (232) of each strut (230) and the inner surface (226) of the nozzle (220).

6. The jet noise suppressor (200) of claim 5 wherein each strut (230) comprises a swept back shape.

7. The jet noise suppressor (200) of claim 6 wherein:

the front surface of each strut (230) comprises a convex shape; and

the rear surface of each strut (230) comprises a concave shape.

8. The jet noise suppressor (200) of claim 1 wherein:

the inner surface (226) of the nozzle (220) comprises a concave shape; and

the outer surface (228) of the nozzle (220) comprises a convex shape.

9. The jet noise suppressor (200) of claim 1, wherein the nozzle (220) comprises a first nozzle (220), the jet noise suppressor (200) further comprising a second nozzle (220), the first nozzle (220) and the second nozzle (220) being configured to each be coaxially aligned with a respective jet engine of a pair of jet engines of an aircraft.

10. The jet noise suppressor (200) of any one of claims 1-9 wherein, when the nozzle (220) is coaxially aligned with a jet engine:

an open area between a forward end (222) of the nozzle (220) and a jet engine is configured to accommodate a first air flow passage through the nozzle (220) that exits the aft end (224) of the nozzle (220); and

a plurality of vents (240) are configured to receive a second airflow channel that mixes with the first airflow channel and exits the rear end (224) of the nozzle (220).

Technical Field

Embodiments of the present disclosure relate to a suppressor, and more particularly, to a suppressor for a jet engine, such as an aircraft.

Background

Aircraft, including commercial aircraft and military aircraft, play a vital role in modern society. Commercial aircraft are used to transport people and cargo, thereby promoting commerce. Military aircraft serve a variety of functions, including personnel transportation and law delivery, ensuring strong and effective defense. However, the noise generated by an aircraft engine can be a nuisance, which leads to complaints and is controlled by various statutes or laws.

The noise generated by an aircraft engine varies from aircraft to aircraft. Generally, the noise intensity level is a function of the velocity of the spray plume emitted by the aircraft engine. For example, supersonic aircraft using small bypass ratio turbofan engines produce jet plumes with higher velocity than subsonic aircraft using high bypass ratio engines. Thus, supersonic aircraft tend to produce more jet noise and are more noisy than typical commercial aircraft and cause more community complaints during low altitude operations.

Additionally, the activity of the aircraft may also be an aircraft noise consideration. For example, the Field aircraft Landing practice (Field Carrier Landing Practices) performed by the U.S. navy involves a series of touches and walks using relatively short runways to simulate Landing and take-off from the deck of an aircraft Carrier. The flight patterns and airspeeds required in field aircraft carrier landing practices tend to produce more intense noise than other types of aircraft activity on land. Therefore, field aircraft carrier landing practices have traditionally been performed at remote airports. However, despite these considerations, as exposure to field aircraft carrier landing practices increases and the resulting noise increases, the general public has moved closer to remote airports over time.

Accordingly, it may be desirable to focus on further developments in the field of jet noise suppression while limiting the adverse effects of jet noise suppression on jet engines when in use.

Disclosure of Invention

The systems, methods, apparatuses, and devices of the present disclosure each have several embodiments, no single one of which is solely responsible for its desirable attributes. Without limiting the scope of the disclosure as expressed by the claims which follow, some features will now be discussed briefly. After considering this discussion, and particularly after reading the section entitled "detailed description of certain embodiments" one will understand how the features of this disclosure provide advantages that include jet noise suppression.

In one embodiment, an injection noise suppressor is disclosed. The jet noise suppressor comprises a nozzle having a front end, a rear end, an inner surface, and an outer surface, and a plurality of struts, each strut comprising a base and a distal end, the base of each strut being connected to the inner surface of the nozzle. The jet noise suppressor further comprises a plurality of vents, each vent corresponding to a respective strut. Each vent is formed in the inner surface of the nozzle between the forward end of the nozzle and the base of the respective strut.

In another embodiment, an injection noise suppressor is disclosed. The jet noise suppressor comprises a nozzle having a front end, a rear end, an inner surface, and an outer surface, and a plurality of struts, each strut comprising a base and a distal end, the base of each strut being connected to the inner surface of the nozzle and the distal end of each strut being freestanding such that each strut is connected to the nozzle directly or indirectly only at the base of each strut and the inner surface of the nozzle. The jet noise suppressor further comprises a plurality of vents, each vent corresponding to and extending through a respective strut.

In another embodiment, an aircraft is disclosed. The aircraft includes a jet engine having an aft end that generates an exhaust flow path for propelling the aircraft. The aircraft further includes a jet noise suppressor. The jet noise suppressor comprises a nozzle having a front end, a rear end, an inner surface, and an outer surface, and a plurality of struts, each strut comprising a base and a distal end, the base of each strut being connected to the inner surface of the nozzle. The jet noise suppressor further comprises a plurality of vents, each vent corresponding to a respective strut. Each vent is formed in the inner surface of the nozzle between the forward end of the nozzle and the base of the respective strut. The aircraft further comprises a connecting member to detachably connect the nozzle to the jet engine or to the fuselage of the aircraft.

Drawings

So that the manner in which the above recited features of the present disclosure can be understood in detail, a more particular description, briefly summarized above, may be had by reference to the aspects thereof that are illustrated in the appended drawings. It is to be noted, however, that the appended drawings illustrate only certain typical aspects of this disclosure and are therefore not to be considered limiting of its scope, for the description may admit to other equally effective aspects.

Fig. 1 is a side view of an aircraft including a jet noise suppressor in accordance with one or more embodiments of the present disclosure.

Fig. 2 is a rear perspective view of an aircraft including a jet noise suppressor according to one or more embodiments of the present disclosure.

Fig. 3 is an enlarged rear perspective view of an aircraft including a jet noise suppressor according to one or more embodiments of the present disclosure.

Fig. 4 is a bottom perspective view of an aircraft including a jet noise suppressor in accordance with one or more embodiments of the present disclosure.

Fig. 5 illustrates a front view of an injection noise suppressor according to one or more embodiments of the present disclosure.

Fig. 6 illustrates a front perspective view of a jet noise suppressor in accordance with one or more embodiments of the present disclosure.

Fig. 7 illustrates a rear perspective view of a jet noise suppressor in accordance with one or more embodiments of the present disclosure.

Fig. 8 illustrates a cross-sectional view of an injection noise suppressor and a jet engine according to one or more embodiments of the present disclosure.

Fig. 9 shows a cross-sectional view of an injection noise suppressor for use with a jet engine according to one or more embodiments of the present disclosure.

To facilitate understanding, identical reference numerals have been used, where possible, to designate identical elements that are common to the figures. It is contemplated that elements described in one aspect may be beneficially utilized on other aspects without specific recitation.

Embodiments generally include methods, apparatuses, and systems as substantially described herein with reference to and as illustrated by the accompanying drawings. Numerous other aspects are provided.

To the accomplishment of the foregoing and related ends, one or more aspects comprise the features hereinafter fully described and particularly pointed out in the claims. The following description and the annexed drawings set forth in detail certain illustrative features of the one or more aspects. These features are indicative, however, of but a few of the various ways in which the principles of various aspects may be employed and the description is intended to include all such aspects and their equivalents.