초록 ▼

A gas turbine engine combustion noise suppressor for a jet engine combustor assembly of the annular, cannular, or canannular variety includes a resonant cavity-type or bulk absorber-type noise suppressor. The inner wall of the combustor assembly is configured to couple combustion noise, generated wi

A gas turbine engine combustion noise suppressor for a jet engine combustor assembly of the annular, cannular, or canannular variety includes a resonant cavity-type or bulk absorber-type noise suppressor. The inner wall of the combustor assembly is configured to couple combustion noise, generated within the burner cavity formed by the inner combustor wall, into the airflow duct formed between the inner and outer walls of the combustor assembly. The outer wall is perforated to, in turn, couple the combustion noise from the airflow duct into the resonant cavity-type or bulk absorber-type noise suppressor that is mounted on the portion of the outer wall that is adjacent the burner cavity. The inner combustor wall can include a large number of small acoustic openings and/or a smaller number of larger openings that include airflow barriers to couple the combustion noise into the combustor airflow duct while simultaneously minimizing air flow into the burner cavity from the combustor airflow duct. In other embodiments, a short burner cavity is employed that includes flutes or corrugations in the inner combustor wall to effect mixing of air and combustion products normally accomplished within the aft section of a conventional burner cavity. In each embodiment the structural relationship between the combustor and the noise suppressor modifies the combustion process occurring within a conventional combustor to generate less noise than a conventional combustor. The noise suppressor functions to further reduce the noise level.

대표청구항 ▼

A combined combustor and combustion noise suppressor for a gas turbine engine including a compressor and a turbine, comprising: an outer combustor wall defining an airflow duct between said compressor and said turbine, said outer wall having an inner surface; an inner combustor wall defining a burne

A combined combustor and combustion noise suppressor for a gas turbine engine including a compressor and a turbine, comprising: an outer combustor wall defining an airflow duct between said compressor and said turbine, said outer wall having an inner surface; an inner combustor wall defining a burner cavity, said inner wall being mounted in said airflow duct in spaced relationship from the inner surface of said outer wall, said inner combustor wall including a plurality of air inlet openings therein for placing said burner cavity in fluid communication with said duct, said air inlet openings being dimensioned to allow air flowing through said airflow duct to flow into said burner cavity, said inner combustor wall further including a plurality of acoustic openings for acoustically coupling said burner cavity and said airflow duct, said acoustic openings being dimensioned and arranged to have a low coefficient of discharge relative to the coefficient of discharge of said air inlet openings for minimizing airflow through said acoustic openings and being dimensioned and arranged to allow combustion noise generated within said burner cavity to pass through said acoustic openings and into said airflow duct; and noise suppressing means mounted on said outer combustor wall exterior to said airflow duct for receiving and attenuating noise, said noise suppressing means being located adjacent at least a portion of the acoustic openings in said inner burner wall, said outer combustor wall having a plurality of acoustic openings for acoustically coupling said airflow duct and said noise suppressing means to allow said combustion noise to be transmitted from said burner cavity through said airflow duct and into said noise suppressing means.