US 6,739,120 B2 · Counterrotatable booster compressor assembly for a gas turbine engine

Abstract

A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft, the counterrotatable booster compressor assembly including a first compressor blade row connected to the first drive shaft and a second compressor blade row interdigitated with the first compressor blade row and connected to the second drive shaft. A portion of each fan blade of the second fan blade row extends through a flowpath of the counterrotatable booster compressor so as to function as a compressor blade in the second compressor blade row. The counterrotatable booster compressor further includes a first platform member integral with each fan blade of the second fan blade row at a first location so as to form an inner flowpath for the counterrotatable booster compressor and a second platform member integral with each fan blade of the second fan blade row at a second location so as to form an outer flowpath for the counterrotatable booster compressor.

Claims22

Dependent claims

A fan blade assembly for a gas turbine engine having a counterrotatable fan section and a counterrotatable booster compressor, comprising:

(a) a disk connected to a drive shaft;
(b) a fan blade row retained within said disk;
(c) a first platform member integral with each said fan blade at a first location so as to form an inner flowpath for said counterrotatable booster compressor;
and
(d) a second platform member integral with each said fan blade at a second location so as to form an outer flowpath for said counterrotatable booster compressor;
wherein a portion of each said fan blade extending between said first and second platform members functions as a compressor blade in a compressor blade row of said counterrotatable booster compressor.

3 more elements

A gas turbine engine, comprising:

(a) a high pressure rotor including a high pressure turbine;
(b) a low pressure turbine located aft of said high pressure rotor having counterrotating low pressure inner and outer rotors effective for rotating first and second drive shafts;
(c) a counterrotatable fan section completely forward of said high pressure rotor including a first fan blade row connected to said first drive shaft and a second fan blade row axially spaced from said first fan blade row and connected to said second drive shaft;
and
(d) a counterrotatable booster compressor including a first compressor blade row connected to said first drive shaft and a second compressor blade row interdigitated with said first compressor blade row and connected to said second drive shaft, whereby each low pressure turbine rotor respectively drives both a fan blade row and a compressor blade row;
wherein a portion of each fan blade of said second fan blade row extends through a flowpath of said counterrotatable booster so as to function as a compressor blade in said second compressor blade row of said counterrotatable booster compressor, each fan blade of said second fan blade row further comprising:
(a) a first platform member integral therewith at a first location so as to form an inner flowpath for said counterrotatable booster compressor;
and
(b) a second platform member integral therewith at a second location so as to form an outer flowpath for said counterrotatable booster compressor.

6 more elements

Dependencies are inferred from the claim text.

Counterrotatable booster compressor assembly for a gas turbine engine

Life of this patent

Counterrotatable booster compressor assembly for a gas turbine engine

Life of this patent

Abstract

Claims22