Title:
ガスタービンエンジン圧縮機構造
Document Type and Number:
Japanese Patent JP5676825
Kind Code:
B2
Abstract:
A gas turbine engine includes a fan section, a gear arrangement configured to drive the fan section, a compressor section and a turbine section. The compressor section includes a low pressure compressor section and a high pressure compressor section. The turbine section is configured to drive compressor section and the gear arrangement. An overall pressure ratio, which is provided by a combination of a pressure ratio across said low pressure compressor section and a pressure ratio across said high pressure compressor section, is greater than about 35. The pressure ratio across the low pressure compressor section is between about 3 and about 8 whereas the pressure ratio across the high pressure compressor section is between about 7 and about 15.
Inventors:
ヘイゼル，カール エル．
ストーバック，ジョセフ ビー．
メリー，ブライアン ディー．
スシウ，ガブリエル エル．
ダイ，クリストファー エム．
ストーバック，ジョセフ ビー．
メリー，ブライアン ディー．
スシウ，ガブリエル エル．
ダイ，クリストファー エム．
Application Number:
JP2014528712A
Publication Date:
February 25, 2015
Filing Date:
December 26, 2012
Export Citation:
Assignee:
ユナイテッド テクノロジーズ コーポレイションＵＮＩＴＥＤ ＴＥＣＨＮＯＬＯＧＩＥＳ ＣＯＲＰＯＲＡＴＩＯＮ
International Classes:
F04D27/00; F02C3/107; F02K3/06; F04D19/02; F04D25/04
Attorney, Agent or Firm:
Hiromichi Kobayashi
Tomioka 潔
Tomioka 潔