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CN-121986214-A - Airflow exhaust nozzle with constant outlet cross section and turbine engine equipped with such a nozzle

CN121986214ACN 121986214 ACN121986214 ACN 121986214ACN-121986214-A

Abstract

The invention relates to a turbine engine airflow exhaust nozzle, in particular for an aircraft, extending around a longitudinal axis (X) and along the longitudinal axis (X) between an inlet section (20) and an outlet section (21), the exhaust nozzle being at least partially delimited by a radially outer shell portion (24) and a radially inner shell portion (25), the radially outer shell portion and the radially inner shell portion at least partially forming a flow duct (18,15). According to the invention, a plurality of struts (45) extend radially between the radially outer housing part (24) and the radially inner housing part (25), and the struts (45) are arranged uniformly about the longitudinal axis (X) and have a predetermined height (H1) which is configured such that the radial height (H2) of the outlet section (21) is fixed and constant during operation.

Inventors

  • Jean-Charles Michelle Pierre DiGiovanni
  • Pierre Charles Carroll
  • WILLIAM JOSEPH BOWDEN

Assignees

  • 赛峰短舱公司
  • 通用电气公司

Dates

Publication Date
20260505
Application Date
20241010
Priority Date
20231011

Claims (13)

  1. 1. An exhaust nozzle (17, 19) for a turbine engine airflow, in particular for an aircraft, which exhaust nozzle extends on the one hand around a longitudinal axis (X) and on the other hand along the longitudinal axis (X) between an inlet section (20) and an outlet section (21), which exhaust nozzle is at least partly delimited by a radial outer shell portion (24) and a radial inner shell portion (25) forming at least partly a flow duct (18,15), a plurality of struts (45) extending radially between the radial outer shell portion (24) and the radial inner shell portion (25), and wherein the struts (45) are regularly arranged around the longitudinal axis (X) and have a predetermined height (H1) configured such that the radial height (H2) of the outlet section (21) is fixed and constant in an operating state, characterized in that the struts (45) are arranged at a predetermined axial distance (D1) from the downstream end portion (37) of the radial outer shell portion (24), the axial distance (D1) being equal to three times the radial height (H1) of the outlet section, preferably equal to seven times the radial height (D1).
  2. 2. The exhaust nozzle (17, 19) according to the preceding claim, wherein the radial height (H2) of the outlet section (21) is between 15mm and 50mm, preferably between 25mm and 30 mm.
  3. 3. The exhaust nozzle (17, 19) according to any one of the preceding claims, comprising an outer structure (22) attached to the radially outer shell portion (24) extending the outer structure downstream along the longitudinal axis (X) and an inner structure (23) removably attached to the radially inner shell portion (25) extending the inner structure downstream along the longitudinal axis, the inner and outer structures being made of a composite material.
  4. 4. The exhaust nozzle (17, 19) of any of the preceding claims, wherein the radially outer housing part (24) and the radially inner housing part (23) are made of a metallic material.
  5. 5. The exhaust nozzle (17, 19) of any of the preceding claims, wherein each strut (45) has a pneumatic shape shaped to rectify the downstream air flow.
  6. 6. The exhaust nozzle (17, 19) of any of the preceding claims, wherein the radially inner shell portion (25), the radially outer shell portion (24) and the struts (45) are formed as one piece.
  7. 7. The exhaust nozzle (17, 19) of any of claims 1 to 5, wherein the struts (45) are fitted and attached to the radially outer housing portion (24) and the radially inner housing portion (25), which are separate.
  8. 8. The exhaust nozzle (17, 19) of the preceding claim, wherein each strut (45) comprises a heel (65) at a first end, which is housed in a housing (66) provided in a radially inner surface (26) of the radially outer shell (24), and each strut comprises a first corner section (67) at a second end, each first corner section (67) being configured to be assembled with a second corner section (68) carried by the radially inner shell (25) to form a first corner (47') which engages with a first recess (48) carried by the inner structure (23).
  9. 9. The exhaust nozzle (17, 19) of claim 7, wherein each strut (45) includes a heel (65) at a first end configured to bear against a radially outer surface of the radially outer shell portion (24), and each strut includes a fork (73) at a second end, the radially inner shell portion (25) including a plurality of radially extending attachment walls (75), each attachment wall engaged in the fork (73).
  10. 10. The exhaust nozzle (17, 19) according to the preceding claim, wherein the radially outer housing part (24) comprises at least one acoustic panel (70) having a radially outer surface (81) which has a surface continuity with a radially outer surface (35) of the radially inner housing part (25).
  11. 11. Turbine engine (1) according to any one of the preceding claims, comprising at least one exhaust nozzle (17, 19) according to any one of the preceding claims.
  12. 12. Turbine engine (1) according to the preceding claim, characterized in that it comprises an exhaust nozzle comprising a main flow duct (15) in which the main flow generated by a propeller (2) circulates, said propeller (2) also generating a secondary flow which circulates radially around said main flow duct (15).
  13. 13. Turbine engine (1) according to the preceding claim, comprising an exhaust nozzle comprising an external flow duct (18) arranged at least partially radially outside the main flow duct (15), and wherein the radially external flow is circulated from a portion of the main flow (F1) that has passed through at least one compressor (3, 4), the exhaust nozzle being an exhaust nozzle according to any one of claims 1 to 10.

Description

Airflow exhaust nozzle with constant outlet cross section and turbine engine equipped with such a nozzle Technical Field The present invention relates to the field of turbine engines, and in particular to the specific design of an exhaust nozzle through which a flow duct of the air flow of a turbine engine is circulated. Background The prior art includes the following documents US2016/195038A1, US 2022/082331A 1, EP3358174A1 and US2014/311161A1. Climate change is a major concern for many legislation and regulatory authorities around the world. Indeed, various restrictions on carbon emissions have been, are being or will be adopted by the various states. In particular, an aggressive standard applies not only to new aircraft, but also to those already in use for which technical solutions need to be implemented in order for them to comply with the current regulations. For several years, the civil aviation industry has been working on helping to cope with climate change. Technological research efforts have significantly improved the environmental performance of aircraft. The applicant considers the influencing factors of all design and development phases in order to obtain aviation elements and products with lower energy consumption, more environmental protection and moderate environmental impact of integration and use in civil aviation, with the aim of improving the energy efficiency of the aircraft. Accordingly, applicants have been working to reduce their negative impact on climate by employing methods and using benign development and manufacturing methods, and to minimize greenhouse gas emissions, to reduce their active environmental footprint. This ongoing research and development effort has focused on new generation aircraft engines to make aircraft lighter, particularly by using lighter materials and on-board equipment, development of propulsion using electric technology, and use of aviation biofuels as an essential supplement to technological advances. One of these studies relates in particular to a turbine engine equipped with one or more flow ducts for the aerodynamic flow for generating at least part of the thrust. Each exhaust nozzle through which the flow conduit communicates is generally annular and is defined by a radially inner wall and a radially outer wall. These radially inner and outer walls extend along the longitudinal axis of the turbine engine between the inlet and outlet sections. On certain types of turbine engines, particularly those having bypass ratios between 5 and 10, the height separating the two walls is relatively large. However, the height may vary depending on thermal expansion. For other types of turbine engines, the outlet section of the exhaust nozzle defines its performance, particularly if the outlet section is very small (e.g., less than 30 mm). As an example, the outlet section may be used to adjust the flow rate of the airflow circulating in the turbine engine, as well as the operating parameters of certain components of the turbine engine (such as the compressor, which are located at the inlet section of the exhaust nozzle). The slightest variation in the height of the very small outlet section may have a significant impact on the performance and operability of the turbine engine. There is a need to address some or all of the above disadvantages. Disclosure of Invention The object of the present invention is to provide a solution that minimizes the variation in the outlet section of the exhaust nozzle through which the flow duct of the pneumatic air of the turbine engine circulates. According to the invention, this object is achieved by an exhaust nozzle for a turbine engine gas flow, in particular for an aircraft, which extends on the one hand about a longitudinal axis and on the other hand along the longitudinal axis between an inlet section and an outlet section, which is at least partially delimited by a radial outer shell portion and a radial inner shell portion, which at least partially form a flow duct, a plurality of struts extending radially between the radial outer shell portion and the radial inner shell portion, and wherein the struts are regularly arranged about the longitudinal axis and have a predetermined height which is configured such that the radial height of the outlet section is fixed and constant in an operating state. Thus, this solution enables the above-mentioned object to be achieved. In particular, the configuration of the struts enables precise control of the height of the exhaust nozzle at its outlet section and minimizes variation in that height throughout the operating range of the turbine engine. The exhaust nozzle further includes one or more of the following features taken alone or in combination: the radial height of the outlet section is between 15mm and 50mm, and preferably between 25mm and 30 mm. The nozzle comprises an outer structure attached to the radial outer shell portion extending downstream along the longitudinal axis, an